CINXE.COM

<!DOCTYPE html> <html lang="en" dir="ltr"> <head>  <script async src="https://www.googletagmanager.com/gtag/js?id=G-P63WKM1TM1"></script> <script> window.dataLayer = window.dataLayer || []; function gtag(){dataLayer.push(arguments);} gtag('js', new Date()); gtag('config', 'G-P63WKM1TM1'); </script>  <script type="text/javascript" > (function(m,e,t,r,i,k,a){m[i]=m[i]||function(){(m[i].a=m[i].a||[]).push(arguments)}; m[i].l=1*new Date(); for (var j = 0; j < document.scripts.length; j++) {if (document.scripts[j].src === r) { return; }} k=e.createElement(t),a=e.getElementsByTagName(t)[0],k.async=1,k.src=r,a.parentNode.insertBefore(k,a)}) (window, document, "script", "https://mc.yandex.ru/metrika/tag.js", "ym"); ym(55165297, "init", { clickmap:false, trackLinks:true, accurateTrackBounce:true, webvisor:false }); </script> <noscript><div><img src="https://mc.yandex.ru/watch/55165297" style="position:absolute; left:-9999px;" alt="" /></div></noscript>    <title>Search results for: inlet flow angle</title> <meta name="description" content="Search results for: inlet flow angle"> <meta name="keywords" content="inlet flow angle"> <meta name="viewport" content="width=device-width, initial-scale=1, minimum-scale=1, maximum-scale=1, user-scalable=no"> <meta charset="utf-8"> <link href="https://cdn.waset.org/favicon.ico" type="image/x-icon" rel="shortcut icon"> <link href="https://cdn.waset.org/static/plugins/bootstrap-4.2.1/css/bootstrap.min.css" rel="stylesheet"> <link href="https://cdn.waset.org/static/plugins/fontawesome/css/all.min.css" rel="stylesheet"> <link href="https://cdn.waset.org/static/css/site.css?v=150220211555" rel="stylesheet"> </head> <body> <header> <div class="container"> <nav class="navbar navbar-expand-lg navbar-light"> <a class="navbar-brand" href="https://waset.org"> <img src="https://cdn.waset.org/static/images/wasetc.png" alt="Open Science Research Excellence" title="Open Science Research Excellence" /> </a> <button class="d-block d-lg-none navbar-toggler ml-auto" type="button" data-toggle="collapse" data-target="#navbarMenu" aria-controls="navbarMenu" aria-expanded="false" aria-label="Toggle navigation"> <span class="navbar-toggler-icon"></span> </button> <div class="w-100"> <div class="d-none d-lg-flex flex-row-reverse"> <form method="get" action="https://waset.org/search" class="form-inline my-2 my-lg-0"> <input class="form-control mr-sm-2" type="search" placeholder="Search Conferences" value="inlet flow angle" name="q" aria-label="Search"> <button class="btn btn-light my-2 my-sm-0" type="submit"><i class="fas fa-search"></i></button> </form> </div> <div class="collapse navbar-collapse mt-1" id="navbarMenu"> <ul class="navbar-nav ml-auto align-items-center" id="mainNavMenu"> <li class="nav-item"> <a class="nav-link" href="https://waset.org/conferences" title="Conferences in 2024/2025/2026">Conferences</a> </li> <li class="nav-item"> <a class="nav-link" href="https://waset.org/disciplines" title="Disciplines">Disciplines</a> </li> <li class="nav-item"> <a class="nav-link" href="https://waset.org/committees" rel="nofollow">Committees</a> </li> <li class="nav-item dropdown"> <a class="nav-link dropdown-toggle" href="#" id="navbarDropdownPublications" role="button" data-toggle="dropdown" aria-haspopup="true" aria-expanded="false"> Publications </a> <div class="dropdown-menu" aria-labelledby="navbarDropdownPublications"> <a class="dropdown-item" href="https://publications.waset.org/abstracts">Abstracts</a> <a class="dropdown-item" href="https://publications.waset.org">Periodicals</a> <a class="dropdown-item" href="https://publications.waset.org/archive">Archive</a> </div> </li> <li class="nav-item"> <a class="nav-link" href="https://waset.org/page/support" title="Support">Support</a> </li> </ul> </div> </div> </nav> </div> </header> <main> <div class="container mt-4"> <div class="row"> <div class="col-md-9 mx-auto"> <form method="get" action="https://publications.waset.org/abstracts/search"> <div id="custom-search-input"> <div class="input-group"> <i class="fas fa-search"></i> <input type="text" class="search-query" name="q" placeholder="Author, Title, Abstract, Keywords" value="inlet flow angle"> <input type="submit" class="btn_search" value="Search"> </div> </div> </form> </div> </div> <div class="row mt-3"> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Commenced</strong> in January 2007</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Frequency:</strong> Monthly</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Edition:</strong> International</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Paper Count:</strong> 6082</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: inlet flow angle</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6082</span> Mathematical Analysis of Variation in Inlet Shock Wave Angle on Specific Impulse of Scramjet Engine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Shrikant%20Ghadage">Shrikant Ghadage</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Study of shock waves generated in the Scramjet engine is typically restricted to pressure, temperature, density, entropy and Mach number variation across the shock wave. The present work discusses the impact of inlet shock wave angles on the specific impulse of the Scramjet engine. A mathematical analysis has done for the isentropic hypersonic flow of air flowing through a Scramjet with hydrogen fuel at an altitude of 30 km. Analysis has been done in order to get optimum shock wave angle to achieve maximum impulse. Since external drag has excluded from the analysis, the losses due to friction are not considered for the present analysis. When Mach number of the airflow at the entry of the nozzle reaches unity, then that flow is choked. This condition puts limitations on increasing the inlet shock wave angle. As inlet shock wave angle increases, speed of the flow entering into the nozzle decreases, which results in an increase in the specific impulse of the engine. When the speed of the flow at the entry of the nozzle reduces below sonic speed, then there is no further increase in the specific impulse of the engine. Here the Conclusion is the thrust and specific impulse of a scramjet engine, which increases gradually with an increase in inlet shock wave angle up to the condition when airflow speed reaches sonic velocity at the exit of the combustor. In addition to that, variation in drag force at the inlet of the scramjet and variation in hypersonic flow conditions at every stage of the scramjet also studied in order to understand variation on flow characteristics with respect to flow deflection angle. Essentially, it helps in designing inlet profile for the Scramjet engine to achieve optimum specific impulse. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=hypersonic%20flow" title="hypersonic flow">hypersonic flow</a>, <a href="https://publications.waset.org/abstracts/search?q=scramjet" title=" scramjet"> scramjet</a>, <a href="https://publications.waset.org/abstracts/search?q=shock%20waves" title=" shock waves"> shock waves</a>, <a href="https://publications.waset.org/abstracts/search?q=specific%20impulse" title=" specific impulse"> specific impulse</a>, <a href="https://publications.waset.org/abstracts/search?q=mathematical%20analysis" title=" mathematical analysis"> mathematical analysis</a> </p> <a href="https://publications.waset.org/abstracts/104058/mathematical-analysis-of-variation-in-inlet-shock-wave-angle-on-specific-impulse-of-scramjet-engine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/104058.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">168</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6081</span> Experimental and Numerical Investigation of Fluid Flow inside Concentric Heat Exchanger Using Different Inlet Geometry Configurations</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Mohamed%20M.%20Abo%20Elazm">Mohamed M. Abo Elazm</a>, <a href="https://publications.waset.org/abstracts/search?q=Ali%20I.%20Shehata"> Ali I. Shehata</a>, <a href="https://publications.waset.org/abstracts/search?q=Mohamed%20M.%20Khairat%20Dawood"> Mohamed M. Khairat Dawood</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A computational fluid dynamics (CFD) program FLUENT has been used to predict the fluid flow and heat transfer distribution within concentric heat exchangers. The effect of inlet inclination angle has been investigated with Reynolds number range (3000 – 4000) and Pr=0.71. The heat exchanger is fabricated from copper concentric inner tube with a length of 750 mm. The effects of hot to cold inlet flow rate ratio (MH/MC), Reynolds's number and of inlet inclination angle of 30°, 45°, 60° and 90° are considered. The results showed that the numerical prediction shows a good agreement with experimental measurement. The results present an efficient design of concentric tube heat exchanger to enhance the heat transfer by increasing the swirling effect. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=heat%20transfer" title="heat transfer">heat transfer</a>, <a href="https://publications.waset.org/abstracts/search?q=swirling%20effect" title=" swirling effect"> swirling effect</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=inclination%20angle" title=" inclination angle"> inclination angle</a>, <a href="https://publications.waset.org/abstracts/search?q=concentric%20tube%20heat%20exchange" title=" concentric tube heat exchange"> concentric tube heat exchange</a> </p> <a href="https://publications.waset.org/abstracts/71387/experimental-and-numerical-investigation-of-fluid-flow-inside-concentric-heat-exchanger-using-different-inlet-geometry-configurations" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/71387.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">321</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6080</span> Aerodynamic Designing of Supersonic Centrifugal Compressor Stages</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Y.%20Galerkin">Y. Galerkin</a>, <a href="https://publications.waset.org/abstracts/search?q=A.%20Rekstin"> A. Rekstin</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20Soldatova"> K. Soldatova</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Universal modeling method well proven for industrial compressors was applied for design of the high flow rate supersonic stage. Results were checked by ANSYS CFX and NUMECA Fine Turbo calculations. The impeller appeared to be very effective at transonic flow velocities. Stator elements efficiency is acceptable at design Mach numbers too. Their loss coefficient versus inlet flow angle performances correlates well with Universal modeling prediction. The impeller demonstrated ability of satisfactory operation at design flow rate. Supersonic flow behavior in the impeller inducer at the shroud blade to blade surface Φdes deserves additional study. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=centrifugal%20compressor%20stage" title="centrifugal compressor stage">centrifugal compressor stage</a>, <a href="https://publications.waset.org/abstracts/search?q=supersonic%20impeller" title=" supersonic impeller"> supersonic impeller</a>, <a href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle" title=" inlet flow angle"> inlet flow angle</a>, <a href="https://publications.waset.org/abstracts/search?q=loss%20coefficient" title=" loss coefficient"> loss coefficient</a>, <a href="https://publications.waset.org/abstracts/search?q=return%20channel" title=" return channel"> return channel</a>, <a href="https://publications.waset.org/abstracts/search?q=shock%20wave" title=" shock wave"> shock wave</a>, <a href="https://publications.waset.org/abstracts/search?q=vane%20diffuser" title=" vane diffuser"> vane diffuser</a> </p> <a href="https://publications.waset.org/abstracts/18034/aerodynamic-designing-of-supersonic-centrifugal-compressor-stages" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/18034.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">467</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6079</span> Flow Analysis for Different Pelton Turbine Bucket by Applying Computation Fluid Dynamic</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Sedat%20Yayla">Sedat Yayla</a>, <a href="https://publications.waset.org/abstracts/search?q=Azhin%20Abdullah"> Azhin Abdullah</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In the process of constructing hydroelectric power plants, the Pelton turbine, which is characterized by its simple manufacturing and construction, is performed in high head and low water flow. Parameters of the turbine have to be comprised in the designing process for obtaining hydraulic turbine with the highest efficiency during different operating conditions. The present investigation applied three-dimensional computational fluid dynamics (CFD). In addition, the bucket of Pelton turbine models with different splitter angle and inlet velocity values were examined for determining the force and visualizing the flow pattern on the bucket. The study utilized two diverse bucket models at various inlet velocities (20, 25, 30,35and 40m/s) and four different splitter angles (55, 75,90and 115 degree) for finding out the impacts of every single parameter on the effective force on the bucket. The acquired outcomes revealed that there is a linear relationship between force and inlet velocity on the bucket. Furthermore, the results also uncovered that the relationship between splitter angle and force on the bucket is linear until 90 degree. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=bucket%20design" title="bucket design">bucket design</a>, <a href="https://publications.waset.org/abstracts/search?q=computational%20fluid%20dynamics%20%28CFD%29" title=" computational fluid dynamics (CFD)"> computational fluid dynamics (CFD)</a>, <a href="https://publications.waset.org/abstracts/search?q=free%20surface%20flow" title=" free surface flow"> free surface flow</a>, <a href="https://publications.waset.org/abstracts/search?q=two-phase%20flow" title=" two-phase flow"> two-phase flow</a>, <a href="https://publications.waset.org/abstracts/search?q=volume%20of%20fluid%20%28VOF%29" title=" volume of fluid (VOF)"> volume of fluid (VOF)</a> </p> <a href="https://publications.waset.org/abstracts/74893/flow-analysis-for-different-pelton-turbine-bucket-by-applying-computation-fluid-dynamic" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/74893.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">271</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6078</span> Effects of Inlet Distorted Flows on the Performance of an Axial Compressor</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Asad%20Islam">Asad Islam</a>, <a href="https://publications.waset.org/abstracts/search?q=Khalid%20Parvez"> Khalid Parvez</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Compressor fans in modern aircraft engines are of considerate importance, as they provide majority of thrust required by the aircraft. Their challenging environment is frequently subjected to non-uniform inflow conditions. These conditions could be either due to the flight operating requirements such as take-off and landing, wake interference from aircraft fuselage or cross-flow wind conditions. So, in highly maneuverable flights regimes of fighter aircrafts affects the overall performance of an engine. Since the flow in compressor of an aircraft application is highly sensitive because of adverse pressure gradient due to different flow orientations of the aircraft. Therefore, it is prone to unstable operations. This paper presents the study that focuses on axial compressor response to inlet flow orientations for the range of angles as 0 to 15 degrees. For this purpose, NASA Rotor-37 was taken and CFD mesh was developed. The compressor characteristics map was generated for the design conditions of pressure ratio of 2.106 with the rotor operating at rotational velocity of 17188.7 rpm using CFD simulating environment of ANSYS-CFX®. The grid study was done to see the effects of mesh upon computational solution. Then, the mesh giving the best results, (when validated with the available experimental NASA’s results); was used for further distortion analysis. The flow in the inlet nozzle was given angle orientations ranging from 0 to 15 degrees. The CFD results are analyzed and discussed with respect to stall margin and flow separations due to induced distortions. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=axial%20compressor" title="axial compressor">axial compressor</a>, <a href="https://publications.waset.org/abstracts/search?q=distortions" title=" distortions"> distortions</a>, <a href="https://publications.waset.org/abstracts/search?q=angle" title=" angle"> angle</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=ANSYS-CFX%C2%AE" title=" ANSYS-CFX®"> ANSYS-CFX®</a>, <a href="https://publications.waset.org/abstracts/search?q=bladegen%C2%AE" title=" bladegen®"> bladegen®</a> </p> <a href="https://publications.waset.org/abstracts/46801/effects-of-inlet-distorted-flows-on-the-performance-of-an-axial-compressor" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/46801.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">456</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6077</span> Calculation of the Supersonic Air Intake with the Optimization of the Shock Wave System </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Elena%20Vinogradova">Elena Vinogradova</a>, <a href="https://publications.waset.org/abstracts/search?q=Aleksei%20Pleshakov"> Aleksei Pleshakov</a>, <a href="https://publications.waset.org/abstracts/search?q=Aleksei%20Yakovlev"> Aleksei Yakovlev</a> </p> <p class="card-text"><strong>Abstract:</strong></p> During the flight of a supersonic aircraft under various conditions (altitude, Mach, etc.), it becomes necessary to coordinate the operating modes of the air intake and engine. On the supersonic aircraft, it’s been done by changing various control factors (the angle of rotation of the wedge panels and etc.). This paper investigates the possibility of using modern optimization methods to determine the optimal position of the supersonic air intake wedge panels in order to maximize the total pressure recovery coefficient. Modern software allows us to conduct auto-optimization, which determines the optimal position of the control elements of the investigated product to achieve its maximum efficiency. In this work, the flow in the supersonic aircraft inlet has investigated and optimized the operation of the flaps of the supersonic inlet in an aircraft in a 2-D setting. This work has done using ANSYS CFX software. The supersonic aircraft inlet is a flat adjustable external compression inlet. The braking surface is made in the form of a three-stage wedge. The IOSO NM software package was chosen for optimization. Change in the position of the panels of the input device is carried out by changing the angle between the first and second steps of the three-stage wedge. The position of the rest of the panels is changed automatically. Within the framework of the presented work, the position of the moving air intake panel was optimized under fixed flight conditions of the aircraft under a certain engine operating mode. As a result of the numerical modeling, the distribution of total pressure losses was obtained for various cases of the engine operation, depending on the incoming flow velocity and the flight altitude of the aircraft. The results make it possible to obtain the maximum total pressure recovery coefficient under given conditions. Also, the initial geometry was set with a certain angle between the first and second wedge panels. Having performed all the calculations, as well as the subsequent optimization of the aircraft input device, it can be concluded that the initial angle was set sufficiently close to the optimal angle. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=optimal%20angle" title="optimal angle">optimal angle</a>, <a href="https://publications.waset.org/abstracts/search?q=optimization" title=" optimization"> optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=supersonic%20air%20intake" title=" supersonic air intake"> supersonic air intake</a>, <a href="https://publications.waset.org/abstracts/search?q=total%20pressure%20recovery%20coefficient" title=" total pressure recovery coefficient"> total pressure recovery coefficient</a> </p> <a href="https://publications.waset.org/abstracts/135524/calculation-of-the-supersonic-air-intake-with-the-optimization-of-the-shock-wave-system" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/135524.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">242</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6076</span> CFD Analysis of the Blood Flow in Left Coronary Bifurcation with Variable Angulation</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Midiya%20Khademi">Midiya Khademi</a>, <a href="https://publications.waset.org/abstracts/search?q=Ali%20Nikoo"> Ali Nikoo</a>, <a href="https://publications.waset.org/abstracts/search?q=Shabnam%20Rahimnezhad%20Baghche%20Jooghi"> Shabnam Rahimnezhad Baghche Jooghi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Cardiovascular diseases (CVDs) are the main cause of death globally. Most CVDs can be prevented by avoiding habitual risk factors. Separate from the habitual risk factors, there are some inherent factors in each individual that can increase the risk potential of CVDs. Vessel shapes and geometry are influential factors, having great impact on the blood flow and the hemodynamic behavior of the vessels. In the present study, the influence of bifurcation angle on blood flow characteristics is studied. In order to approach this topic, by simplifying the details of the bifurcation, three models with angles 30°, 45°, and 60° were created, then by using CFD analysis, the response of these models for stable flow and pulsatile flow was studied. In the conducted simulation in order to eliminate the influence of other geometrical factors, only the angle of the bifurcation was changed and other parameters remained constant during the research. Simulations are conducted under dynamic and stable condition. In the stable flow simulation, a steady velocity of 0.17 m/s at the inlet plug was maintained and in dynamic simulations, a typical LAD flow waveform is implemented. The results show that the bifurcation angle has an influence on the maximum speed of the flow. In the stable flow condition, increasing the angle lead to decrease the maximum flow velocity. In the dynamic flow simulations, increasing the bifurcation angle lead to an increase in the maximum velocity. Since blood flow has pulsatile characteristics, using a uniform velocity during the simulations can lead to a discrepancy between the actual results and the calculated results. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=coronary%20artery" title="coronary artery">coronary artery</a>, <a href="https://publications.waset.org/abstracts/search?q=cardiovascular%20disease" title=" cardiovascular disease"> cardiovascular disease</a>, <a href="https://publications.waset.org/abstracts/search?q=bifurcation" title=" bifurcation"> bifurcation</a>, <a href="https://publications.waset.org/abstracts/search?q=atherosclerosis" title=" atherosclerosis"> atherosclerosis</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=artery%20wall%20shear%20stress" title=" artery wall shear stress"> artery wall shear stress</a> </p> <a href="https://publications.waset.org/abstracts/106497/cfd-analysis-of-the-blood-flow-in-left-coronary-bifurcation-with-variable-angulation" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/106497.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">164</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6075</span> One Dimensional Reactor Modeling for Methanol Steam Reforming to Hydrogen</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Hongfang%20Ma">Hongfang Ma</a>, <a href="https://publications.waset.org/abstracts/search?q=Mingchuan%20Zhou"> Mingchuan Zhou</a>, <a href="https://publications.waset.org/abstracts/search?q=Haitao%20Zhang"> Haitao Zhang</a>, <a href="https://publications.waset.org/abstracts/search?q=Weiyong%20Ying"> Weiyong Ying</a> </p> <p class="card-text"><strong>Abstract:</strong></p> One dimensional pseudo-homogenous modeling has been performed for methanol steam reforming reactor. The results show that the models can well predict the industrial data. The reactor had minimum temperature along axial because of endothermic reaction. Hydrogen productions and temperature profiles along axial were investigated regarding operation conditions such as inlet mass flow rate and mass fraction of methanol, inlet temperature of external thermal oil. Low inlet mass flow rate of methanol, low inlet temperature, and high mass fraction of methanol decreased minimum temperature along axial. Low inlet mass flow rate of methanol, high mass fraction of methanol, and high inlet temperature of thermal oil made cold point forward. Low mass fraction, high mass flow rate, and high inlet temperature of thermal oil increased hydrogen production. One dimensional models can be a guide for industrial operation. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=reactor" title="reactor">reactor</a>, <a href="https://publications.waset.org/abstracts/search?q=modeling" title=" modeling"> modeling</a>, <a href="https://publications.waset.org/abstracts/search?q=methanol" title=" methanol"> methanol</a>, <a href="https://publications.waset.org/abstracts/search?q=steam%20reforming" title=" steam reforming"> steam reforming</a> </p> <a href="https://publications.waset.org/abstracts/86646/one-dimensional-reactor-modeling-for-methanol-steam-reforming-to-hydrogen" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/86646.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">298</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6074</span> Flow Behavior and Performances of Centrifugal Compressor Stage Vaneless Diffusers</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Y.Galerkin">Y.Galerkin</a>, <a href="https://publications.waset.org/abstracts/search?q=O.%20Solovieva"> O. Solovieva</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Flow parameters are calculated in vaneless diffusers with relative width 0,014 – 0,10 constant along radii. Inlet flow angles and similarity criteria were varied. Information about flow structure is presented – meridian streamlines configuration, information on flow full development, flow separation. Polytrophic efficiency, loss and recovery coefficient are used to compare diffusers’ effectiveness. The sample of narrow diffuser optimization by conical walls application is presented. Three tampered variants of a wide diffuser are compared too. The work is made in the R&D laboratory “Gas dynamics of turbo machines” of the TU SPb. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=vaneless%20diffuser" title="vaneless diffuser">vaneless diffuser</a>, <a href="https://publications.waset.org/abstracts/search?q=relative%20width" title=" relative width"> relative width</a>, <a href="https://publications.waset.org/abstracts/search?q=flow%20angle" title=" flow angle"> flow angle</a>, <a href="https://publications.waset.org/abstracts/search?q=flow%20separation" title=" flow separation"> flow separation</a>, <a href="https://publications.waset.org/abstracts/search?q=loss%20coefficient" title=" loss coefficient"> loss coefficient</a>, <a href="https://publications.waset.org/abstracts/search?q=similarity%20criteria" title=" similarity criteria"> similarity criteria</a> </p> <a href="https://publications.waset.org/abstracts/15996/flow-behavior-and-performances-of-centrifugal-compressor-stage-vaneless-diffusers" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/15996.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">490</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6073</span> Numerical Study of Flow Characteristics and Performance of 14-X B Inlet with Blunted Cowl-Lip</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Sergio%20N.%20P.%20Lait%C3%B3n">Sergio N. P. Laitón</a>, <a href="https://publications.waset.org/abstracts/search?q=Paulo%20G.%20P.%20Toro"> Paulo G. P. Toro</a>, <a href="https://publications.waset.org/abstracts/search?q=Jo%C3%A3o%20F.%20%20Martos"> João F. Martos</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A numerical study has been carried out to investigate the flow characteristics and performance of the 14-X B inlet with blunted cowl-lip. The Brazilian aerospace hypersonic vehicle 14-X B is a technology demonstrator of a hypersonic air-breathing propulsion system, based on supersonic combustion ramjet (scramjet). It is designed for Earth's atmospheric flight at Mach number of 6 and an altitude of 30 km. Currently, it is under development in the aerothermodynamics and hypersonic Professor Henry T. Nagamatsu laboratory at Advanced Studies Institute (IEAv). Numerical simulations were conducted at nominal freestream Mach number and altitude for two cowl-lip blunting radius and several angles of attack close to horizontal flight. The results show that the shock interference behavior on the blunted cowl-lip change with the angle of attack and blunted radius. The type VI or V together with III shock interferences are more likely to occur simultaneously at small negative angles of attack. When the inlet operates in positive angles of attack higher to 1, no shock interference occurs, only the bow shock conditions. The results indicate a high air pressure at beginning of the combustor and higher pressure recovery with 2 mm radius and positives angles of attack. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=blunted%20cowl-lip" title="blunted cowl-lip">blunted cowl-lip</a>, <a href="https://publications.waset.org/abstracts/search?q=hypersonic%20inlet" title=" hypersonic inlet"> hypersonic inlet</a>, <a href="https://publications.waset.org/abstracts/search?q=inlet%20unstart" title=" inlet unstart"> inlet unstart</a>, <a href="https://publications.waset.org/abstracts/search?q=shock%20interference" title=" shock interference"> shock interference</a> </p> <a href="https://publications.waset.org/abstracts/59537/numerical-study-of-flow-characteristics-and-performance-of-14-x-b-inlet-with-blunted-cowl-lip" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/59537.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">323</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6072</span> Diabatic Flow of Sub-Cooled R-600a Inside a Capillary Tube: Concentric Configuration</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ravi%20Kumar">Ravi Kumar</a>, <a href="https://publications.waset.org/abstracts/search?q=Santhosh%20Kumar%20Dubba"> Santhosh Kumar Dubba </a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper presents an experimental study of a diabatic flow of R-600a through a concentric configured capillary tube suction line heat exchanger. The details of experimental facility for testing the diabatic capillary tube with different inlet sub-cooling degree and pressure are discussed. The effect of coil diameter, capillary length, capillary tube diameter, sub-cooling degree and inlet pressure on mass flow rate are presented. The degree of sub-cooling at the inlet of capillary tube is varied from 3-20°C. The refrigerant mass flow rate is scattered up with rising of pressure. A semi-empirical correlation to predict the mass flow rate of R-600a flowing through a diabatic capillary tube is proposed for sub-cooled inlet conditions. The proposed correlation predicts measured data with an error band of ±20 percent. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=diabatic" title="diabatic">diabatic</a>, <a href="https://publications.waset.org/abstracts/search?q=capillary%20tube" title=" capillary tube"> capillary tube</a>, <a href="https://publications.waset.org/abstracts/search?q=concentric" title=" concentric"> concentric</a>, <a href="https://publications.waset.org/abstracts/search?q=R-600a" title=" R-600a"> R-600a</a> </p> <a href="https://publications.waset.org/abstracts/81743/diabatic-flow-of-sub-cooled-r-600a-inside-a-capillary-tube-concentric-configuration" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/81743.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">204</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6071</span> Aerodynamic Investigation of Rear Vehicle by Geometry Variations on the Backlight Angle</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Saud%20Hassan">Saud Hassan</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper shows simulation for the prediction of the flow around the backlight angle of the passenger vehicle. The CFD simulations are carried out on different car models. The Ahmed model “bluff body” used as the stander model to study aerodynamics of the backlight angle. This paper described the airflow over the different car models with different backlight angles and also on the Ahmed model to determine the trailing vortices with the varying backlight angle of a passenger vehicle body. The CFD simulation is carried out with the Ahmed body which has simplified car model mainly used in automotive industry to investigate the flow over the car body surface. The main goal of the simulation is to study the behavior of trailing vortices of these models. In this paper the air flow over the slant angle of 0,5o, 12.5o, 20o, 30o, 40o are considered. As investigating on the rear backlight angle two dimensional flows occurred at the rear slant, on the other hand when the slant angle is 30o the flow become three dimensional. Above this angle sudden drop occurred in drag. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamics" title="aerodynamics">aerodynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=Ahemd%20vehicle" title=" Ahemd vehicle "> Ahemd vehicle </a>, <a href="https://publications.waset.org/abstracts/search?q=backlight%20angle" title=" backlight angle"> backlight angle</a>, <a href="https://publications.waset.org/abstracts/search?q=finite%20element%20method" title=" finite element method "> finite element method </a> </p> <a href="https://publications.waset.org/abstracts/26384/aerodynamic-investigation-of-rear-vehicle-by-geometry-variations-on-the-backlight-angle" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/26384.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">781</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6070</span> A Numerical Investigation of Flow Maldistribution in Inlet Header Configuration of Plate Fin Heat Exchanger</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Appasaheb%20Raul">Appasaheb Raul</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Numerical analysis of a plate fin heat exchanger accounting for the effect of fluid flow maldistribution on the inlet header configuration of the heat exchanger is investigated. It is found that the flow maldistribution is very significant in normal to the flow direction. Various inlet configuration has been studied for various Reynolds Number. By the study, a modified header configuration is proposed and simulated. The two-dimensional parameters are used to evaluate the flow non-uniformity in the header, global flow maldistribution parameter (Sg), and Velocity Ratio (θ). A series of velocity vectors and streamline graphs at different cross-section are achieved and studied qualitatively with experimental results in the literature. The numerical result indicates that the flow maldistribution is serious in the conventional header while in the improved configuration less maldistribution occurs. The flow maldistribution parameter (Sg) and velocity ratio (θ) is reduced in improved configuration. The vortex decreases compared to that of the conventional configuration so the energy and pressure loss is reduced. The improved header can effectively enhance the efficiency of plate fin heat exchanger and uniformity of flow distribution. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=global%20flow%20maldistribution%20parameter" title="global flow maldistribution parameter">global flow maldistribution parameter</a>, <a href="https://publications.waset.org/abstracts/search?q=Sg" title=" Sg"> Sg</a>, <a href="https://publications.waset.org/abstracts/search?q=velocity%20ratio" title=" velocity ratio"> velocity ratio</a>, <a href="https://publications.waset.org/abstracts/search?q=plate%20fin%20heat%20exchanger" title=" plate fin heat exchanger"> plate fin heat exchanger</a>, <a href="https://publications.waset.org/abstracts/search?q=fluent%2014.5" title=" fluent 14.5"> fluent 14.5</a> </p> <a href="https://publications.waset.org/abstracts/34028/a-numerical-investigation-of-flow-maldistribution-in-inlet-header-configuration-of-plate-fin-heat-exchanger" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/34028.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">526</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6069</span> Field Synergy Analysis of Combustion Characteristics in the Afterburner of Solid Oxide Fuel Cell System</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Shing-Cheng%20Chang">Shing-Cheng Chang</a>, <a href="https://publications.waset.org/abstracts/search?q=Cheng-Hao%20Yang"> Cheng-Hao Yang</a>, <a href="https://publications.waset.org/abstracts/search?q=Wen-Sheng%20Chang"> Wen-Sheng Chang</a>, <a href="https://publications.waset.org/abstracts/search?q=Chih-Chia%20Lin"> Chih-Chia Lin</a>, <a href="https://publications.waset.org/abstracts/search?q=Chun-Han%20Li"> Chun-Han Li</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The solid oxide fuel cell (SOFC) is a promising green technology which can achieve a high electrical efficiency. Due to the high operating temperature of SOFC stack, the off-gases at high temperature from anode and cathode outlets are introduced into an afterburner to convert the chemical energy into thermal energy by combustion. The heat is recovered to preheat the fresh air and fuel gases before they pass through the stack during the SOFC power generation system operation. For an afterburner of the SOFC system, the temperature control with a good thermal uniformity is important. A burner with a well-designed geometry usually can achieve a satisfactory performance. To design an afterburner for an SOFC system, the computational fluid dynamics (CFD) simulation is adoptable. In this paper, the hydrogen combustion characteristics in an afterburner with simple geometry are studied by using CFD. The burner is constructed by a cylinder chamber with the configuration of a fuel gas inlet, an air inlet, and an exhaust outlet. The flow field and temperature distributions inside the afterburner under different fuel and air flow rates are analyzed. To improve the temperature uniformity of the afterburner during the SOFC system operation, the flow paths of anode/cathode off-gases are varied by changing the positions of fuels and air inlet channel to improve the heat and flow field synergy in the burner furnace. Because the air flow rate is much larger than the fuel gas, the flow structure and heat transfer in the afterburner is dominated by the air flow path. The present work studied the effects of fluid flow structures on the combustion characteristics of an SOFC afterburner by three simulation models with a cylindrical combustion chamber and a tapered outlet. All walls in the afterburner are assumed to be no-slip and adiabatic. In each case, two set of parameters are simulated to study the transport phenomena of hydrogen combustion. The equivalence ratios are in the range of 0.08 to 0.1. Finally, the pattern factor for the simulation cases is calculated to investigate the effect of gas inlet locations on the temperature uniformity of the SOFC afterburner. The results show that the temperature uniformity of the exhaust gas can be improved by simply adjusting the position of the gas inlet. The field synergy analysis indicates the design of the fluid flow paths should be in the way that can significantly contribute to the heat transfer, i.e. the field synergy angle should be as small as possible. In the study cases, the averaged synergy angle of the burner is about 85̊, 84̊, and 81̊ respectively. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=afterburner" title="afterburner">afterburner</a>, <a href="https://publications.waset.org/abstracts/search?q=combustion" title=" combustion"> combustion</a>, <a href="https://publications.waset.org/abstracts/search?q=field%20synergy" title=" field synergy"> field synergy</a>, <a href="https://publications.waset.org/abstracts/search?q=solid%20oxide%20fuel%20cell" title=" solid oxide fuel cell"> solid oxide fuel cell</a> </p> <a href="https://publications.waset.org/abstracts/98344/field-synergy-analysis-of-combustion-characteristics-in-the-afterburner-of-solid-oxide-fuel-cell-system" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/98344.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">137</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6068</span> Prediction of the Aerodynamic Stall of a Helicopter’s Main Rotor Using a Computational Fluid Dynamics Analysis</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Assel%20Thami%20Lahlou">Assel Thami Lahlou</a>, <a href="https://publications.waset.org/abstracts/search?q=Soufiane%20Stouti"> Soufiane Stouti</a>, <a href="https://publications.waset.org/abstracts/search?q=Ismail%20Lagrat"> Ismail Lagrat</a>, <a href="https://publications.waset.org/abstracts/search?q=Hamid%20Mounir"> Hamid Mounir</a>, <a href="https://publications.waset.org/abstracts/search?q=Oussama%20Bouazaoui"> Oussama Bouazaoui</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The purpose of this research work is to predict the helicopter from stalling by finding the minimum and maximum values that the pitch angle can take in order to fly in a hover state condition. The stall of a helicopter in hover occurs when the pitch angle is too small to generate the thrust required to support its weight or when the critical angle of attack that gives maximum lift is reached or exceeded. In order to find the minimum pitch angle, a 3D CFD simulation was done in this work using ANSYS FLUENT as the CFD solver. We started with a small value of the pitch angle θ, and we kept increasing its value until we found the thrust coefficient required to fly in a hover state and support the weight of the helicopter. For the CFD analysis, the Multiple Reference Frame (MRF) method with k-ε turbulent model was used to study the 3D flow around the rotor for θmin. On the other hand, a 2D simulation of the airfoil NACA 0012 was executed with a velocity inlet Vin=ΩR/2 to visualize the flow at the location span R/2 of the disk rotor using the Spallart-Allmaras turbulent model. Finding the critical angle of attack at this position will give us the ability to predict the stall in hover flight. The results obtained will be exposed later in the article. This study was so useful in analyzing the limitations of the helicopter’s main rotor and thus, in predicting accidents that can lead to a lot of damage. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic" title="aerodynamic">aerodynamic</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=helicopter" title=" helicopter"> helicopter</a>, <a href="https://publications.waset.org/abstracts/search?q=stall" title=" stall"> stall</a>, <a href="https://publications.waset.org/abstracts/search?q=blades" title=" blades"> blades</a>, <a href="https://publications.waset.org/abstracts/search?q=main%20rotor" title=" main rotor"> main rotor</a>, <a href="https://publications.waset.org/abstracts/search?q=minimum%20pitch%20angle" title=" minimum pitch angle"> minimum pitch angle</a>, <a href="https://publications.waset.org/abstracts/search?q=maximum%20pitch%20angle" title=" maximum pitch angle"> maximum pitch angle</a> </p> <a href="https://publications.waset.org/abstracts/186086/prediction-of-the-aerodynamic-stall-of-a-helicopters-main-rotor-using-a-computational-fluid-dynamics-analysis" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/186086.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">81</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6067</span> CFD Simulation of the Inlet Pressure Effects on the Cooling Capacity Enhancement for Vortex Tube with Couple Vortex Chambers</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Nader%20Pourmahmoud">Nader Pourmahmoud</a>, <a href="https://publications.waset.org/abstracts/search?q=Amir%20Hassanzadeh"> Amir Hassanzadeh</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This article investigates the effects of inlet pressure in a newly introduced vortex tube which has been equipped with an additional vortex chamber. A 3-D compressible turbulent flow computation has been carried out toward analysis of complex flow field in this apparatus. Numerical results of flows are derived by utilizing the standard k-ε turbulence model for analyzing high rotating complex flow field. The present research has focused on cooling effect and given a characteristics curve for minimum cool temperature. In addition, the effect of inlet pressure for both chambers has been studied in details. To be presented numerical results show that the effect of inlet pressure in second chamber has more important role in improving the performance of the vortex tube than first one. By increasing the pressure in the second chamber, cold outlet temperature reaches a higher decrease. When both chambers are fed with high pressure fluid, best operation condition of vortex tube occurs. However, it is not possible to feed both chambers with high pressure due to the conditions of working environment. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=energy%20separation" title="energy separation">energy separation</a>, <a href="https://publications.waset.org/abstracts/search?q=inlet%20pressure" title=" inlet pressure"> inlet pressure</a>, <a href="https://publications.waset.org/abstracts/search?q=numerical%20simulation" title=" numerical simulation"> numerical simulation</a>, <a href="https://publications.waset.org/abstracts/search?q=vortex%20chamber" title=" vortex chamber"> vortex chamber</a>, <a href="https://publications.waset.org/abstracts/search?q=vortex%20tube" title=" vortex tube"> vortex tube</a> </p> <a href="https://publications.waset.org/abstracts/18358/cfd-simulation-of-the-inlet-pressure-effects-on-the-cooling-capacity-enhancement-for-vortex-tube-with-couple-vortex-chambers" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/18358.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">371</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6066</span> CFD Analysis of a Two-Sided Windcatcher Inlet/Outlet Ducts’ Height in Ventilation Flow through a Three Dimensional Room</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Amirreza%20Niktash">Amirreza Niktash</a>, <a href="https://publications.waset.org/abstracts/search?q=B.%20P.%20Huynh"> B. P. Huynh</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A windcatcher is a structure fitted on the roof of a building for providing natural ventilation by using wind power; it exhausts the inside stale air to the outside and supplies the outside fresh air into the interior space of the building working by pressure difference between outside and inside of the building and using ventilation principles of passive stacks and wind tower, respectively. In this paper, the effect of different heights of inlet/outlets’ ducts of a two-sided windcatcher on the flow rate, flow velocity and flow pattern through a three-dimensional room fitted with the windcatcher are investigated and analysed by using RANS CFD technique and applying standard K-ε turbulence model via a commercial computational fluid dynamics (CFD) software package. The achieved results show that the inlet/outlet ducts height strongly affects flow rate, flow velocity and flow pattern especially in the living area of the room when the wind velocity is not too low. The results are confirmed by the experimental test for constructed scaled model in the laboratory and it develops the two-sided windcatcher’s performance in ventilation applications. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=CFD" title="CFD">CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=RANS" title=" RANS"> RANS</a>, <a href="https://publications.waset.org/abstracts/search?q=ventilation" title=" ventilation"> ventilation</a>, <a href="https://publications.waset.org/abstracts/search?q=windcatcher" title=" windcatcher"> windcatcher</a> </p> <a href="https://publications.waset.org/abstracts/18751/cfd-analysis-of-a-two-sided-windcatcher-inletoutlet-ducts-height-in-ventilation-flow-through-a-three-dimensional-room" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/18751.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">429</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6065</span> A Counter-flow Vortex Tube With Energy Separation: An Experimental Study and CFD Analysis</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Li%CC%87zan%20Mahmood%20Khorsheed%20Zangana">Li̇zan Mahmood Khorsheed Zangana</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Experimental and numerical investigations have been carried out to study the mechanism of separation energy and flow phenomena in the counter-flow vortex tube. This manuscript presents a complete comparison between the experimental investigation and CFD analysis. The experimental model tested under different inlet pressures. Three-dimensional numerical modelling using the k-ε model. The results show any increase in both cold mass fraction and inlet pressure caused to increase ΔTc, and the maximum ΔTc value occurs at P = 6 bar. The coefficient of performance (COP) of two important factors in the vortex tube have been evaluated, which ranged from 0.25 to 0.74. The maximum axial velocity is 93, where it occurs at the tube axis close the inlet exit (Z/L=0.2). The results showed a good agreement for experimental and numerical analysis. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=counter%20flow" title="counter flow">counter flow</a>, <a href="https://publications.waset.org/abstracts/search?q=vortex%20tube" title=" vortex tube"> vortex tube</a>, <a href="https://publications.waset.org/abstracts/search?q=computational%20fluid%20dynamics%20analysis" title=" computational fluid dynamics analysis"> computational fluid dynamics analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=energy%20separation" title=" energy separation"> energy separation</a>, <a href="https://publications.waset.org/abstracts/search?q=experimental%20study" title=" experimental study"> experimental study</a> </p> <a href="https://publications.waset.org/abstracts/169576/a-counter-flow-vortex-tube-with-energy-separation-an-experimental-study-and-cfd-analysis" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/169576.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">79</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6064</span> Numerical Investigation of the Diffuser: Geometrical Parameters Effect on Flow Characteristics for Diffuser Augmented Wind Turbine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Hany%20El%20Said%20Fawaz">Hany El Said Fawaz</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This study deals with numerical simulation using a commercial package 'ANSYS FLUENT 14.5' for flow characteristics of a flanged diffuser wind turbine. Influence of geometrical parameters such as flange height, diffuser length, and expansion angle on the lift and drag performance were investigated. As the angle of expansion increases, a considerable flow acceleration through the diffuser occur at expansion angle ranged from 0° and 12° due to the presence of undisturbed streamlines. after that flow circulation is developed near the diffuser outlet and increase with increasing expansion angle which causes a negligible effect of expansion angle. The effect of diffuser length on flow behavior shows that when the diffuser length ratio is less than 1.25, flow acceleration is observed and increased with diffuser length ratio. After this value, the flow field at diffuser outlet is characterized by a recirculation zone. The diffuser flange has an impact effect of the flow behavior as a low pressure zone is developed behind the flange, while a high pressure zone is generated in front of it. As the flange height increase, the intensity of both low and high pressure regions increase which tend to accelerate the flow inside the diffuser till flange height ratio reaches to 0.75. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=wind%20turbine" title="wind turbine">wind turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=flanged%20diffuser" title=" flanged diffuser"> flanged diffuser</a>, <a href="https://publications.waset.org/abstracts/search?q=expansion%20angle" title=" expansion angle"> expansion angle</a>, <a href="https://publications.waset.org/abstracts/search?q=diffuser%20length" title=" diffuser length"> diffuser length</a> </p> <a href="https://publications.waset.org/abstracts/76610/numerical-investigation-of-the-diffuser-geometrical-parameters-effect-on-flow-characteristics-for-diffuser-augmented-wind-turbine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/76610.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">248</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6063</span> Cavitating Flow through a Venturi Using Computational Fluid Dynamics</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Imane%20Benghalia">Imane Benghalia</a>, <a href="https://publications.waset.org/abstracts/search?q=Mohammed%20Zamoum"> Mohammed Zamoum</a>, <a href="https://publications.waset.org/abstracts/search?q=Rachid%20Boucetta"> Rachid Boucetta</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Hydrodynamic cavitation is a complex physical phenomenon that appears in hydraulic systems (pumps, turbines, valves, Venturi tubes, etc.) when the fluid pressure decreases below the saturated vapor pressure. The works carried out in this study aimed to get a better understanding of the cavitating flow phenomena. For this, we have numerically studied a cavitating bubbly flow through a Venturi nozzle. The cavitation model is selected and solved using a commercial computational fluid dynamics (CFD) code. The obtained results show the effect of the inlet pressure (10, 7, 5, and 2 bars) of the Venturi on pressure, the velocity of the fluid flow, and the vapor fraction. We found that the inlet pressure of the Venturi strongly affects the evolution of the pressure, velocity, and vapor fraction formation in the cavitating flow. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=cavitating%20flow" title="cavitating flow">cavitating flow</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=phase%20change" title=" phase change"> phase change</a>, <a href="https://publications.waset.org/abstracts/search?q=venturi" title=" venturi"> venturi</a> </p> <a href="https://publications.waset.org/abstracts/166565/cavitating-flow-through-a-venturi-using-computational-fluid-dynamics" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/166565.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">84</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6062</span> Computational Analysis of Variation in Thrust of Oblique Detonation Ramjet Engine With Adaptive Inlet</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Aditya">Aditya</a>, <a href="https://publications.waset.org/abstracts/search?q=Ganapati%20Joshi"> Ganapati Joshi</a>, <a href="https://publications.waset.org/abstracts/search?q=Vinod%20Kumar"> Vinod Kumar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> IN THE MODERN-WARFARE ERA, THE PRIME REQUIREMENT IS A HIGH SPEED AND MACH NUMBER. WHEN THE MISSILES STRIKE IN THE HYPERSONIC REGIME THE OPPONENT CAN DETECT IT WITH THE ANTI-DEFENSE SYSTEM BUT CAN NOT STOP IT FROM CAUSING DAMAGE. SO, TO ACHIEVE THE SPEEDS OF THIS LEVEL THERE ARE TWO ENGINES THAT ARE AVAILABLE WHICH CAN WORK IN THIS REGION ARE RAMJET AND SCRAMJET. THE PROBLEM WITH RAMJET STARTS TO OCCUR WHEN MACH NUMBER EXCEEDS 4 AS THE STATIC PRESSURE AT THE INLET BECOMES EQUAL TO THE EXIT PRESSURE. SO, SCRAMJET ENGINE DEALS WITH THIS PROBLEM AS IT NEARLY HAS THE SAME WORKING BUT HERE THE FLOW IS NOT MUCH SLOWED DOWN AS COMPARED TO RAMJET IN THE DIFFUSER BUT IT SUFFERS FROM THE PROBLEMS SUCH AS INLET BUZZ, THERMAL CHOCKING, MIXING OF FUEL AND OXIDIZER, THERMAL HEATING, AND MANY MORE. HERE THE NEW ENGINE IS DEVELOPED ON THE SAME PRINCIPLE AS THE SCRAMJET ENGINE BUT BURNING HAPPENS DUE TO DETONATION INSTEAD OF DEFLAGRATION. THE PROBLEM WITH THE ENGINE STARTS WHEN THE MACH NUMBER BECOMES VARIABLE AND THE INLET GEOMETRY IS FIXED AND THIS LEADS TO INLET SPILLAGE WHICH WILL AFFECT THE THRUST ADVERSELY. SO, HERE ADAPTIVE INLET IS MADE OF SHAPE MEMORY ALLOYS WHICH WILL ENHANCE THE INLET MASS FLOW RATE AS WELL AS THRUST. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=detonation" title="detonation">detonation</a>, <a href="https://publications.waset.org/abstracts/search?q=ramjet%20engine" title=" ramjet engine"> ramjet engine</a>, <a href="https://publications.waset.org/abstracts/search?q=shape%20memory%20alloy" title=" shape memory alloy"> shape memory alloy</a>, <a href="https://publications.waset.org/abstracts/search?q=ignition%20delay" title=" ignition delay"> ignition delay</a>, <a href="https://publications.waset.org/abstracts/search?q=shock-boundary%20layer%20interaction" title=" shock-boundary layer interaction"> shock-boundary layer interaction</a>, <a href="https://publications.waset.org/abstracts/search?q=eddy%20dissipation" title=" eddy dissipation"> eddy dissipation</a>, <a href="https://publications.waset.org/abstracts/search?q=asymmetric%20nozzle" title=" asymmetric nozzle"> asymmetric nozzle</a> </p> <a href="https://publications.waset.org/abstracts/149070/computational-analysis-of-variation-in-thrust-of-oblique-detonation-ramjet-engine-with-adaptive-inlet" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/149070.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">102</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6061</span> Comparison on Electrode and Ground Arrangements Effect on Heat Transfer under Electric Force in a Channel and a Cavity Flow</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Suwimon%20Saneewong%20Na%20Ayuttaya">Suwimon Saneewong Na Ayuttaya</a>, <a href="https://publications.waset.org/abstracts/search?q=Chainarong%20Chaktranond"> Chainarong Chaktranond</a>, <a href="https://publications.waset.org/abstracts/search?q=Phadungsak%20Rattanadecho"> Phadungsak Rattanadecho</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This study numerically investigates the effects of Electrohydrodynamic on flow patterns and heat transfer enhancement within a cavity which is on the lower wall of channel. In this simulation, effects of using ground wire and ground plate on the flow patterns are compared. Moreover, the positions of electrode wire respecting with ground are tested in the range of angles θ = 0 - 180°. High electrical voltage exposes to air is 20 kV. Bulk mean velocity and temperature of inlet air are controlled at 0.1 m/s and 60°C, respectively. The result shows when electric field is applied, swirling flow is appeared in the channel. In addition, swirling flow patterns in the main flow of using ground plate are widely spreader than that of using ground wire. Moreover, direction of swirling flow also affects the flow pattern and heat transfer in a cavity. These cause the using ground wire to give the maximum temperature and heat transfer higher than using ground plate. Furthermore, when the angle is at θ = 60°, high shear flow effect is obtained. This results show high strength of swirling flow and effective heat transfer enhancement. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=swirling%20flow" title="swirling flow">swirling flow</a>, <a href="https://publications.waset.org/abstracts/search?q=heat%20transfer" title=" heat transfer"> heat transfer</a>, <a href="https://publications.waset.org/abstracts/search?q=electrohydrodynamic" title=" electrohydrodynamic"> electrohydrodynamic</a>, <a href="https://publications.waset.org/abstracts/search?q=numerical%20analysis" title=" numerical analysis"> numerical analysis</a> </p> <a href="https://publications.waset.org/abstracts/9317/comparison-on-electrode-and-ground-arrangements-effect-on-heat-transfer-under-electric-force-in-a-channel-and-a-cavity-flow" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/9317.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">292</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6060</span> Investigation of the Flow Characteristics in a Catalytic Muffler with Perforated Inlet Cone</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Gyo%20Woo%20Lee">Gyo Woo Lee</a>, <a href="https://publications.waset.org/abstracts/search?q=Man%20Young%20Kim"> Man Young Kim</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Emission regulations for diesel engines are being strengthened and it is impossible to meet the standards without exhaust after-treatment systems. Lack of the space in many diesel vehicles, however, make it difficult to design and install stand-alone catalytic converters such as DOC, DPF, and SCR in the vehicle exhaust systems. Accordingly, those have been installed inside the muffler to save the space, and referred to the catalytic muffler. However, that has complex internal structure with perforated plate and pipe for noise and monolithic catalyst for emission reduction. For this reason, flow uniformity and pressure drop, which affect efficiency of catalyst and engine performance, respectively, should be examined when the catalytic muffler is designed. In this work, therefore, the flow uniformity and pressure drop to improve the performance of the catalytic converter and the engine have been numerically investigated by changing various design parameters such as inlet shape, porosity, and outlet shape of the muffler using the three-dimensional turbulent flow of the incompressible, non-reacting, and steady state inside the catalytic muffler. Finally, it can be found that the shape, in which the muffler has perforated pipe inside the inlet part, has higher uniformity index and lower pressure drop than others considered in this work. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=catalytic%20muffler" title="catalytic muffler">catalytic muffler</a>, <a href="https://publications.waset.org/abstracts/search?q=perforated%20inlet%20cone" title=" perforated inlet cone"> perforated inlet cone</a>, <a href="https://publications.waset.org/abstracts/search?q=catalysts" title=" catalysts"> catalysts</a>, <a href="https://publications.waset.org/abstracts/search?q=perforated%20pipe" title=" perforated pipe"> perforated pipe</a>, <a href="https://publications.waset.org/abstracts/search?q=flow%20uniformity" title=" flow uniformity"> flow uniformity</a>, <a href="https://publications.waset.org/abstracts/search?q=pressure%20drop" title=" pressure drop"> pressure drop</a> </p> <a href="https://publications.waset.org/abstracts/8517/investigation-of-the-flow-characteristics-in-a-catalytic-muffler-with-perforated-inlet-cone" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/8517.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">326</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6059</span> The Effect of Inlet Baffle Position in Improving the Efficiency of Oil and Water Gravity Separator Tanks </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Haitham%20A.%20Hussein">Haitham A. Hussein</a>, <a href="https://publications.waset.org/abstracts/search?q=Rozi%20Abdullah"> Rozi Abdullah</a>, <a href="https://publications.waset.org/abstracts/search?q=Issa%20Saket"> Issa Saket</a>, <a href="https://publications.waset.org/abstracts/search?q=Md.%20Azlin"> Md. Azlin</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The gravitational effect has been extensively applied to separate oil from water in water and wastewater treatment systems. The maximum oil globules removal efficiency is improved by obtaining the best flow uniformity in separator tanks. This study used 2D computational fluid dynamics (CFD) to investigate the effect of different inlet baffle positions inside the separator tank. Laboratory experiment has been conducted, and the measured velocity fields which were by Nortek Acoustic Doppler Velocimeter (ADV) are used to verify the CFD model. Computational investigation results indicated that the construction of an inlet baffle in a suitable location provides the minimum recirculation zone volume, creates the best flow uniformity, and dissipates kinetic energy in the oil and water separator tank. Useful formulas were predicted to design the oil and water separator tanks geometry based on an experimental model. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=oil%2Fwater%20separator%20tanks" title="oil/water separator tanks">oil/water separator tanks</a>, <a href="https://publications.waset.org/abstracts/search?q=inlet%20baffles" title=" inlet baffles"> inlet baffles</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=VOF" title=" VOF"> VOF</a> </p> <a href="https://publications.waset.org/abstracts/52725/the-effect-of-inlet-baffle-position-in-improving-the-efficiency-of-oil-and-water-gravity-separator-tanks" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/52725.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">367</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6058</span> Investigation and Perfection of Centrifugal Compressor Stages by CFD Methods</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Y.%20Galerkin">Y. Galerkin</a>, <a href="https://publications.waset.org/abstracts/search?q=L.%20Marenina"> L. Marenina</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Stator elements «Vane diffuser + crossover + return channel» of stages with different specific speed were investigated by CFD calculations. The regime parameter was introduced to present efficiency and loss coefficient performance of all elements together. Flow structure demonstrated advantages and disadvantages of design. Flow separation in crossovers was eliminated by its shape modification. Efficiency increased visibly. Calculated CFD performances are in acceptable correlation with predicted ones by engineering design method. The information obtained is useful for design method better calibration. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=vane%20diffuser" title="vane diffuser">vane diffuser</a>, <a href="https://publications.waset.org/abstracts/search?q=return%20channel" title=" return channel"> return channel</a>, <a href="https://publications.waset.org/abstracts/search?q=crossover" title=" crossover"> crossover</a>, <a href="https://publications.waset.org/abstracts/search?q=efficiency" title=" efficiency"> efficiency</a>, <a href="https://publications.waset.org/abstracts/search?q=loss%20coefficient" title=" loss coefficient"> loss coefficient</a>, <a href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle" title=" inlet flow angle"> inlet flow angle</a> </p> <a href="https://publications.waset.org/abstracts/16297/investigation-and-perfection-of-centrifugal-compressor-stages-by-cfd-methods" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/16297.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">430</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6057</span> Unconfined Laminar Nanofluid Flow and Heat Transfer around a Square Cylinder with an Angle of Incidence </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Rafik%20Bouakkaz">Rafik Bouakkaz</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A finite-volume method simulation is used to investigate two dimensional unsteady flow of nanofluids and heat transfer characteristics past a square cylinder inclined with respect to the main flow in the laminar regime. The computations are carried out of nanoparticle volume fractions varying from 0 ≤ ∅ ≤ 5% for an inclination angle in the range 0° ≤ δ ≤ 45° at a Reynolds number of 100. The variation of stream line and isotherm patterns are presented for the above range of conditions. Also, it is noticed that the addition of nanoparticles enhances the heat transfer. Hence, the local Nusselt number is found to increase with increasing value of the concentration of nanoparticles for the fixed value of the inclination angle. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=copper%20nanoparticles" title="copper nanoparticles">copper nanoparticles</a>, <a href="https://publications.waset.org/abstracts/search?q=heat%20transfer" title=" heat transfer"> heat transfer</a>, <a href="https://publications.waset.org/abstracts/search?q=square%20cylinder" title=" square cylinder"> square cylinder</a>, <a href="https://publications.waset.org/abstracts/search?q=inclination%20angle" title=" inclination angle"> inclination angle</a> </p> <a href="https://publications.waset.org/abstracts/101220/unconfined-laminar-nanofluid-flow-and-heat-transfer-around-a-square-cylinder-with-an-angle-of-incidence" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/101220.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">190</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6056</span> Effect of Adverse Pressure Gradient on a Fluctuating Velocity over the Co-Flow Jet Airfoil</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Morteza%20Mirhosseini">Morteza Mirhosseini</a>, <a href="https://publications.waset.org/abstracts/search?q=Amir%20B.%20Khoshnevis"> Amir B. Khoshnevis </a> </p> <p class="card-text"><strong>Abstract:</strong></p> The boundary layer separation and new active flow control of a NACA 0025 airfoil were studied experimentally. This new flow control is sometimes known as a co-flow jet (cfj) airfoil. This paper presents the fluctuating velocity in a wall jet over the co-flow jet airfoil subjected to an adverse pressure gradient and a curved surface. In these results, the fluctuating velocity at the inner part increasing by increased the angle of attack up to 12<sup>o</sup> and this has due to the jet energized, while the angle of attack 20<sup>o</sup> has different. The airfoil cord based Reynolds number has 10<sup>5</sup>. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=adverse%20pressure%20gradient" title="adverse pressure gradient">adverse pressure gradient</a>, <a href="https://publications.waset.org/abstracts/search?q=fluctuating%20velocity" title=" fluctuating velocity"> fluctuating velocity</a>, <a href="https://publications.waset.org/abstracts/search?q=wall%20jet" title=" wall jet"> wall jet</a>, <a href="https://publications.waset.org/abstracts/search?q=co-flow%20jet%20airfoil" title=" co-flow jet airfoil"> co-flow jet airfoil</a> </p> <a href="https://publications.waset.org/abstracts/37038/effect-of-adverse-pressure-gradient-on-a-fluctuating-velocity-over-the-co-flow-jet-airfoil" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/37038.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">492</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6055</span> CFD Modeling of Air Stream Pressure Drop inside Combustion Air Duct of Coal-Fired Power Plant with and without Airfoil</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Pakawhat%20Khumkhreung">Pakawhat Khumkhreung</a>, <a href="https://publications.waset.org/abstracts/search?q=Yottana%20Khunatorn"> Yottana Khunatorn</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The flow pattern inside rectangular intake air duct of 300 MW lignite coal-fired power plant is investigated in order to analyze and reduce overall inlet system pressure drop. The system consists of the 45-degree inlet elbow, the flow instrument, the 90-degree mitered elbow and fans, respectively. The energy loss in each section can be determined by Bernoulli’s equation and ASHRAE standard table. Hence, computational fluid dynamics (CFD) is used in this study based on Navier-Stroke equation and the standard k-epsilon turbulence modeling. Input boundary condition is 175 kg/s mass flow rate inside the 11-m<sup>2</sup> cross sectional duct. According to the inlet air flow rate, the Reynolds number of airstream is 2.7x10<sup>6</sup> (based on the hydraulic duct diameter), thus the flow behavior is turbulence. The numerical results are validated with the real operation data. It is found that the numerical result agrees well with the operating data, and dominant loss occurs at the flow rate measurement device. Normally, the air flow rate is measured by the airfoil and it gets high pressure drop inside the duct. To overcome this problem, the airfoil is planned to be replaced with the other type measuring instrument, such as the average pitot tube which generates low pressure drop of airstream. The numerical result in case of average pitot tube shows that the pressure drop inside the inlet airstream duct is decreased significantly. It should be noted that the energy consumption of inlet air system is reduced too. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=airfoil" title="airfoil">airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=average%20pitot%20tube" title=" average pitot tube"> average pitot tube</a>, <a href="https://publications.waset.org/abstracts/search?q=combustion%20air" title=" combustion air"> combustion air</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=pressure%20drop" title=" pressure drop"> pressure drop</a>, <a href="https://publications.waset.org/abstracts/search?q=rectangular%20duct" title=" rectangular duct"> rectangular duct</a> </p> <a href="https://publications.waset.org/abstracts/73573/cfd-modeling-of-air-stream-pressure-drop-inside-combustion-air-duct-of-coal-fired-power-plant-with-and-without-airfoil" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/73573.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">157</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6054</span> Bubble Growth in a Two Phase Upward Flow in a Miniature Tube</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=R.%20S.%20Hassani">R. S. Hassani</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Chikh"> S. Chikh</a>, <a href="https://publications.waset.org/abstracts/search?q=L.%20Tadrist"> L. Tadrist</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Radev"> S. Radev</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A bubbly flow in a vertical miniature tube is analyzed theoretically. The liquid and gas phase are co-current flowing upward. The gas phase is injected via a nozzle whose inner diameter is 0.11mm and it is placed on the axis of the tube. A force balance is applied on the bubble at its detachment. The set of governing equations are solved by use of Mathematica software. The bubble diameter and the bubble generation frequency are determined for various inlet phase velocities represented by the inlet mass quality. The results show different behavior of bubble growth and detachment depending on the tube size. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=two%20phase%20flow" title="two phase flow">two phase flow</a>, <a href="https://publications.waset.org/abstracts/search?q=bubble%20growth" title=" bubble growth"> bubble growth</a>, <a href="https://publications.waset.org/abstracts/search?q=mini-channel" title=" mini-channel"> mini-channel</a>, <a href="https://publications.waset.org/abstracts/search?q=generation%20frequency" title=" generation frequency"> generation frequency</a> </p> <a href="https://publications.waset.org/abstracts/7322/bubble-growth-in-a-two-phase-upward-flow-in-a-miniature-tube" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/7322.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">432</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">6053</span> Experimental Study on Performance of a Planar Membrane Humidifier for a Proton Exchange Membrane Fuel Cell Stack</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Chen-Yu%20Chen">Chen-Yu Chen</a>, <a href="https://publications.waset.org/abstracts/search?q=Wei-Mon%20Yan"> Wei-Mon Yan</a>, <a href="https://publications.waset.org/abstracts/search?q=Chi-Nan%20Lai"> Chi-Nan Lai</a>, <a href="https://publications.waset.org/abstracts/search?q=Jian-Hao%20Su"> Jian-Hao Su</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The proton exchange membrane fuel cell (PEMFC) becomes more important as an alternative energy source recently. Maintaining proper water content in the membrane is one of the key requirements for optimizing the PEMFC performance. The planar membrane humidifier has the advantages of simple structure, low cost, low-pressure drop, light weight, reliable performance and good gas separability. Thus, it is a common external humidifier for PEMFCs. In this work, a planar membrane humidifier for kW-scale PEMFCs is developed successfully. The heat and mass transfer of humidifier is discussed, and its performance is analyzed in term of dew point approach temperature (DPAT), water vapor transfer rate (WVTR) and water recovery ratio (WRR). The DPAT of the humidifier with the counter flow approach reaches about 6°C under inlet dry air of 50°C and 60% RH and inlet humid air of 70°C and 100% RH. The rate of pressure loss of the humidifier is 5.0×10² Pa/min at the torque of 7 N-m, which reaches the standard of commercial planar membrane humidifiers. From the tests, it is found that increasing the air flow rate increases the WVTR. However, the DPAT and the WRR are not improved by increasing the WVTR as the air flow rate is higher than the optimal value. In addition, increasing the inlet temperature or the humidity of dry air decreases the WVTR and the WRR. Nevertheless, the DPAT is improved at elevated inlet temperatures or humidities of dry air. Furthermore, the performance of the humidifier with the counter flow approach is better than that with the parallel flow approach. The DPAT difference between the two flow approaches reaches up to 8 °C. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=heat%20and%20mass%20transfer" title="heat and mass transfer">heat and mass transfer</a>, <a href="https://publications.waset.org/abstracts/search?q=humidifier%20performance" title=" humidifier performance"> humidifier performance</a>, <a href="https://publications.waset.org/abstracts/search?q=PEM%20fuel%20cell" title=" PEM fuel cell"> PEM fuel cell</a>, <a href="https://publications.waset.org/abstracts/search?q=planar%20membrane%20humidifier" title=" planar membrane humidifier"> planar membrane humidifier</a> </p> <a href="https://publications.waset.org/abstracts/75515/experimental-study-on-performance-of-a-planar-membrane-humidifier-for-a-proton-exchange-membrane-fuel-cell-stack" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/75515.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">307</span> </span> </div> </div> <ul class="pagination"> <li class="page-item disabled"><span class="page-link">&lsaquo;</span></li> <li class="page-item active"><span class="page-link">1</span></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=2">2</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=3">3</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=4">4</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=5">5</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=6">6</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=7">7</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=8">8</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=9">9</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=10">10</a></li> <li class="page-item disabled"><span class="page-link">...</span></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=202">202</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=203">203</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=inlet%20flow%20angle&page=2" rel="next">&rsaquo;</a></li> </ul> </div> </main> <footer> <div id="infolinks" class="pt-3 pb-2"> <div class="container"> <div style="background-color:#f5f5f5;" class="p-3"> <div class="row"> <div class="col-md-2"> <ul class="list-unstyled"> About <li><a href="https://waset.org/page/support">About Us</a></li> <li><a href="https://waset.org/page/support#legal-information">Legal</a></li> <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/WASET-16th-foundational-anniversary.pdf">WASET celebrates its 16th foundational anniversary</a></li> </ul> </div> <div class="col-md-2"> <ul class="list-unstyled"> Account <li><a href="https://waset.org/profile">My Account</a></li> </ul> </div> <div class="col-md-2"> <ul class="list-unstyled"> Explore <li><a href="https://waset.org/disciplines">Disciplines</a></li> <li><a href="https://waset.org/conferences">Conferences</a></li> <li><a href="https://waset.org/conference-programs">Conference Program</a></li> <li><a href="https://waset.org/committees">Committees</a></li> <li><a href="https://publications.waset.org">Publications</a></li> </ul> </div> <div class="col-md-2"> <ul class="list-unstyled"> Research <li><a href="https://publications.waset.org/abstracts">Abstracts</a></li> <li><a href="https://publications.waset.org">Periodicals</a></li> <li><a href="https://publications.waset.org/archive">Archive</a></li> </ul> </div> <div class="col-md-2"> <ul class="list-unstyled"> Open Science <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/Open-Science-Philosophy.pdf">Open Science Philosophy</a></li> <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/Open-Science-Award.pdf">Open Science Award</a></li> <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/Open-Society-Open-Science-and-Open-Innovation.pdf">Open Innovation</a></li> <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/Postdoctoral-Fellowship-Award.pdf">Postdoctoral Fellowship Award</a></li> <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/Scholarly-Research-Review.pdf">Scholarly Research Review</a></li> </ul> </div> <div class="col-md-2"> <ul class="list-unstyled"> Support <li><a href="https://waset.org/page/support">Support</a></li> <li><a href="https://waset.org/profile/messages/create">Contact Us</a></li> <li><a href="https://waset.org/profile/messages/create">Report Abuse</a></li> </ul> </div> </div> </div> </div> </div> <div class="container text-center"> <hr style="margin-top:0;margin-bottom:.3rem;"> <a href="https://creativecommons.org/licenses/by/4.0/" target="_blank" class="text-muted small">Creative Commons Attribution 4.0 International License</a> <div id="copy" class="mt-2">© 2024 World Academy of Science, Engineering and Technology</div> </div> </footer> <a href="javascript:" id="return-to-top"><i class="fas fa-arrow-up"></i></a> <div class="modal" id="modal-template"> <div class="modal-dialog"> <div class="modal-content"> <div class="row m-0 mt-1"> <div class="col-md-12"> <button type="button" class="close" data-dismiss="modal" aria-label="Close"><span aria-hidden="true">×</span></button> </div> </div> <div class="modal-body"></div> </div> </div> </div> <script src="https://cdn.waset.org/static/plugins/jquery-3.3.1.min.js"></script> <script src="https://cdn.waset.org/static/plugins/bootstrap-4.2.1/js/bootstrap.bundle.min.js"></script> <script src="https://cdn.waset.org/static/js/site.js?v=150220211556"></script> <script> jQuery(document).ready(function() { /*jQuery.get("https://publications.waset.org/xhr/user-menu", function (response) { jQuery('#mainNavMenu').append(response); });*/ jQuery.get({ url: "https://publications.waset.org/xhr/user-menu", cache: false }).then(function(response){ jQuery('#mainNavMenu').append(response); }); }); </script> </body> </html>