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angle</title> <meta name="description" content="Search results for: flow angle"> <meta name="keywords" content="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" 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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="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> 5932</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: 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">5932</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">5931</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">5930</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">5929</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">5928</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">5927</span> Computational Fluid Dynamics Analysis of an RC Airplane Wing Using a NACA 2412 Profile at Different Angle of Attacks</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Huseyin%20Gokberk">Huseyin Gokberk</a>, <a href="https://publications.waset.org/abstracts/search?q=Shian%20Gao"> Shian Gao</a> </p> <p class="card-text"><strong>Abstract:</strong></p> CFD analysis of the relationship between the coefficients of lift and drag with respect to the angle of attack on a NACA 2412 wing section of an RC plane is conducted. Both the 2D and 3D models are investigated with the turbulence model. The 2D analysis has a free stream velocity of 10m/s at different AoA of 0°, 2°, 5°, 10°, 12°, and 15°. The induced drag and drag coefficient increased throughout the changes in angles even after the critical angle had been exceeded, whereas the lift force and coefficient of lift increased but had a limit at the critical stall angle, which results in values to reduce sharply. Turbulence flow characteristics are analysed around the aerofoil with the additions caused due to a finite 3D model. 3D results highlight how wing tip vortexes develop and alter the flow around the wing with the effects of the tapered configuration. <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=turbulence%20modelling" title=" turbulence modelling"> turbulence modelling</a>, <a href="https://publications.waset.org/abstracts/search?q=aerofoil" title=" aerofoil"> aerofoil</a>, <a href="https://publications.waset.org/abstracts/search?q=angle%20of%20attack" title=" angle of attack"> angle of attack</a> </p> <a href="https://publications.waset.org/abstracts/104536/computational-fluid-dynamics-analysis-of-an-rc-airplane-wing-using-a-naca-2412-profile-at-different-angle-of-attacks" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/104536.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">225</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">5926</span> Flow Visualization around a Rotationally Oscillating Cylinder</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Cemre%20Polat">Cemre Polat</a>, <a href="https://publications.waset.org/abstracts/search?q=Mustafa%20Soyler"> Mustafa Soyler</a>, <a href="https://publications.waset.org/abstracts/search?q=Bulent%20Yaniktepe"> Bulent Yaniktepe</a>, <a href="https://publications.waset.org/abstracts/search?q=Coskun%20Ozalp"> Coskun Ozalp</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this study, it was aimed to control the flow actively by giving an oscillating rotational motion to a vertically placed cylinder, and flow characteristics were determined. In the study, firstly, the flow structure around the flat cylinder was investigated with dye experiments, and then the cylinders with different oscillation angles (θ = 60°, θ = 120°, and θ = 180°) and different rotation speeds (15 rpm and 30 rpm) the flow structure around it was examined. Thus, the effectiveness of oscillation and rotation speed in flow control has been investigated. In the dye experiments, the dye/water mixture obtained by mixing Rhodamine 6G in powder form with water, which shines under laser light and allows detailed observation of the flow structure, was used. During the experiments, the dye was injected into the flow with the help of a thin needle at a distance that would not affect the flow from the front of the cylinder. In dye experiments, 100 frames per second were taken with a Canon brand EOS M50 (24MP) digital mirrorless camera at a resolution of 1280 * 720 pixels. Then, the images taken were analyzed, and the pictures representing the flow structure for each experiment were obtained. As a result of the study, it was observed that no separation points were formed at 180° swing angle at 15 rpm speed, 120° and 180° swing angle at 30 rpm, and the flow was controlled according to the fixed cylinder. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=active%20flow%20control" title="active flow control">active flow control</a>, <a href="https://publications.waset.org/abstracts/search?q=cylinder" title=" cylinder"> cylinder</a>, <a href="https://publications.waset.org/abstracts/search?q=flow%20visualization%20rotationally%20oscillating" title=" flow visualization rotationally oscillating"> flow visualization rotationally oscillating</a> </p> <a href="https://publications.waset.org/abstracts/130645/flow-visualization-around-a-rotationally-oscillating-cylinder" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/130645.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">175</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">5925</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">5924</span> Study of Bifurcation Curve with Aspect Ratio at Low Reynolds Number</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Amit%20K.%20Singh">Amit K. Singh</a>, <a href="https://publications.waset.org/abstracts/search?q=Subhankar%20Sen"> Subhankar Sen</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The bifurcation curve of separation in steady two-dimensional viscous flow past an elliptic cylinder is studied by varying the angle of incidence (α) with different aspect ratio (ratio of minor to major axis). The solutions are based on numerical investigation, using finite element analysis, of the Navier-Stokes equations for incompressible flow. Results are presented for Reynolds number up to 50 and angle of incidence varies from 0° to 90°. Range of aspect ratio (Ar) is from 0.1 to 1 (in steps of 0.1) and flow is considered as unbounded flow. Bifurcation curve represents the locus of Reynolds numbers (Res) at which flow detaches or separates from the surface of the body at a given α and Ar. In earlier studies, effect of Ar on laminar separation curve or bifurcation curve is limited for Ar = 0.1, 0.2, 0.5 and 0.8. Some results are also available at α = 90° and 45°. The present study attempts to provide a systematic data and clear understanding on the effect of Ar at bifurcation curve and its point of maxima. In addition, issues regarding location of separation angle and maximum ratio of coefficient of lift to drag are studied. We found that nature of curve, separation angle and maximum ratio of lift to drag changes considerably with respect to change in Ar. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aspect%20ratio" title="aspect ratio">aspect ratio</a>, <a href="https://publications.waset.org/abstracts/search?q=bifurcation%20curve" title=" bifurcation curve"> bifurcation curve</a>, <a href="https://publications.waset.org/abstracts/search?q=elliptic%20cylinder" title=" elliptic cylinder"> elliptic cylinder</a>, <a href="https://publications.waset.org/abstracts/search?q=GMRES" title=" GMRES"> GMRES</a>, <a href="https://publications.waset.org/abstracts/search?q=stabilized%20finite-element" title=" stabilized finite-element"> stabilized finite-element</a> </p> <a href="https://publications.waset.org/abstracts/40551/study-of-bifurcation-curve-with-aspect-ratio-at-low-reynolds-number" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/40551.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">342</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">5923</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">5922</span> Prediction of Turbulent Separated Flow in a Wind Tunel</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Karima%20Boukhadia">Karima Boukhadia</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In the present study, the subsonic flow in an asymmetrical diffuser was simulated numerically using code CFX 11.0 and its generator of grid ICEM CFD. Two models of turbulence were tested: K- ε and K- ω SST. The results obtained showed that the K- ε model singularly over-estimates the speed value close to the wall and that the K- ω SST model is qualitatively in good agreement with the experimental results of Buice and Eaton 1997. They also showed that the separation and reattachment of the fluid on the tilted wall strongly depends on its angle of inclination and that the length of the zone of separation increases with the angle of inclination of the lower wall of the diffuser. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=asymmetric%20diffuser" title="asymmetric diffuser">asymmetric diffuser</a>, <a href="https://publications.waset.org/abstracts/search?q=separation" title=" separation"> separation</a>, <a href="https://publications.waset.org/abstracts/search?q=reattachment" title=" reattachment"> reattachment</a>, <a href="https://publications.waset.org/abstracts/search?q=tilt%20angle" title=" tilt angle"> tilt angle</a>, <a href="https://publications.waset.org/abstracts/search?q=separation%20zone" title=" separation zone"> separation zone</a> </p> <a href="https://publications.waset.org/abstracts/26379/prediction-of-turbulent-separated-flow-in-a-wind-tunel" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/26379.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">576</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">5921</span> Modelling the Effect of Head and Bucket Splitter Angle on the Power Output of a Pelton Turbine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=J.%20A.%20Ujam">J. A. Ujam</a>, <a href="https://publications.waset.org/abstracts/search?q=J.%20L.%20Chukwuneke"> J. L. Chukwuneke</a>, <a href="https://publications.waset.org/abstracts/search?q=C.%20H.%20Achebe"> C. H. Achebe</a>, <a href="https://publications.waset.org/abstracts/search?q=G.%20O.%20R.%20Ikwu"> G. O. R. Ikwu </a> </p> <p class="card-text"><strong>Abstract:</strong></p> This work investigates the effect of head and bucket splitter angle on the power output of a pelton turbine (water turbine), so as to boost the efficiency of Hydro-electric power generation systems. A simulation program was developed using MatLab to depict the force generated by the bucket as the water jet strikes the existing splitter angle (100 to 150) and predicted (10 to 250) splitter angles. Result shows that in addition to the existing splitter angle, six more angles have been investigated for the two operating conditions to give maximum power. The angles are 250, 60 and 190 for high head and low flow with increased pressure while low head and high flow with decreased pressure are 230, 210 and 30 in order of the maximum generating power. The Turbine power output for simulation was more than that of the experiment. This was as a result of their head conditions and the bucket splitter angle. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=bucket%20splitter%20angle" title="bucket splitter angle">bucket splitter angle</a>, <a href="https://publications.waset.org/abstracts/search?q=force" title=" force"> force</a>, <a href="https://publications.waset.org/abstracts/search?q=head" title=" head"> head</a>, <a href="https://publications.waset.org/abstracts/search?q=modelling" title=" modelling"> modelling</a>, <a href="https://publications.waset.org/abstracts/search?q=pelton%20turbine" title=" pelton turbine"> pelton turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=power%20output" title=" power output"> power output</a>, <a href="https://publications.waset.org/abstracts/search?q=shaft%20output" title=" shaft output"> shaft output</a> </p> <a href="https://publications.waset.org/abstracts/21923/modelling-the-effect-of-head-and-bucket-splitter-angle-on-the-power-output-of-a-pelton-turbine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/21923.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">355</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">5920</span> Numerical Investigation into the Effect of Axial Fan Blade Angle on the Fan Performance</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Shayan%20Arefi">Shayan Arefi</a>, <a href="https://publications.waset.org/abstracts/search?q=Qadir%20Esmaili"> Qadir Esmaili</a>, <a href="https://publications.waset.org/abstracts/search?q=Seyed%20Ali%20Jazayeri"> Seyed Ali Jazayeri</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The performance of cooling system affects on efficiency of turbo generators and temperature of winding. Fan blade is one of the most important components of cooling system which plays a significant role in ventilation of generators. Fan performance curve depends on the blade geometry and boundary condition. This paper calculates numerically the performance curve of axial flow fan mounted on turbo generator with 160 MW output power. The numerical calculation was implemented by Ansys-workbench software. The geometrical model of blade was created by bladegen, grid generation and configuration was made by turbogrid and finally, the simulation was implemented by CFX. For the first step, the performance curves consist of pressure rise and efficiency flow rate were calculated in the original angle of blade. Then, by changing the attack angle of blade, the related performance curves were calculated. CFD results for performance curve of each angle show a good agreement with experimental results. Additionally, the field velocity and pressure gradient of flow near the blade were investigated and simulated numerically with varying of angle. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=turbo%20generator" title="turbo generator">turbo generator</a>, <a href="https://publications.waset.org/abstracts/search?q=axial%20fan" title=" axial fan"> axial fan</a>, <a href="https://publications.waset.org/abstracts/search?q=Ansys" title=" Ansys"> Ansys</a>, <a href="https://publications.waset.org/abstracts/search?q=performance" title=" performance"> performance</a> </p> <a href="https://publications.waset.org/abstracts/9953/numerical-investigation-into-the-effect-of-axial-fan-blade-angle-on-the-fan-performance" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/9953.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">365</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">5919</span> A Mathematical Model of Pulsatile Blood Flow through a Bifurcated Artery</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=D.%20Srinivasacharya">D. Srinivasacharya</a>, <a href="https://publications.waset.org/abstracts/search?q=G.%20Madhava%20Rao"> G. Madhava Rao</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this article, the pulsatile flow of blood flow in bifurcated artery with mild stenosis is investigated. Blood is treated to be a micropolar fluid with constant density. The arteries forming bifurcation are assumed to be symmetric about its axes and straight cylinders of restricted length. As the geometry of the stenosed bifurcated artery is irregular, it is changed to regular geometry utilizing the appropriate transformations. The numerical solutions, using the finite difference method, are computed for the flow rate, the shear stress, and the impedance. The influence of time, coupling number, half of the bifurcated angle and Womersley number on shear stress, flow rate and impedance (resistance to the flow) on both sides of the flow divider is shown graphically. It has been observed that the shear stress and flow rate are increasing with increase in the values of Womersley number and bifurcation angle on both sides of the apex. The shear stress is increasing along the inner wall and decreasing along the outer wall of the daughter artery with an increase in the value of coupling number. Further, it has been noticed that the shear stress, flow rate, and impedance are perturbed largely near to the apex in the parent artery due to the presence of backflow near the apex. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=micropolar%20fluid" title="micropolar fluid">micropolar fluid</a>, <a href="https://publications.waset.org/abstracts/search?q=bifurcated%20artery" title=" bifurcated artery"> bifurcated artery</a>, <a href="https://publications.waset.org/abstracts/search?q=stenosis" title=" stenosis"> stenosis</a>, <a href="https://publications.waset.org/abstracts/search?q=back%20flow" title=" back flow"> back flow</a>, <a href="https://publications.waset.org/abstracts/search?q=secondary%20flow" title=" secondary flow"> secondary flow</a>, <a href="https://publications.waset.org/abstracts/search?q=pulsatile%20flow" title=" pulsatile flow"> pulsatile flow</a>, <a href="https://publications.waset.org/abstracts/search?q=Womersley%20number" title=" Womersley number"> Womersley number</a> </p> <a href="https://publications.waset.org/abstracts/86224/a-mathematical-model-of-pulsatile-blood-flow-through-a-bifurcated-artery" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/86224.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">193</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">5918</span> Investigation of Flow Structure over X-45 Type Non-Slender Delta Wing Planform</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=B.%20Yan%C4%B1ktepe">B. Yanıktepe</a>, <a href="https://publications.waset.org/abstracts/search?q=C.%20%C3%96zalp"> C. Özalp</a>, <a href="https://publications.waset.org/abstracts/search?q=B.%20%C5%9Eahin"> B. Şahin</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Delta wing planform is an essential aerodynamic configuration, which could be effectively used at relatively high angles of attack than conventional wings in subsonic flow conditions. The flow over delta wings can be characterized by a pair of leading edge vortices emanating from wing apex. Boundary layer separation causes these vortical structures formed by rolling up of viscous flow sheet. This flow separation mechanism is occurred due to angle of attack and sharp leading edges of the delta wing. Therefore, complexity and variety in planform designs rise to catch the best under abnormal flow conditions. The present experimental study investigates the near surface flow structure and aerodynamic flow characteristics of X-45 type non-slender delta wing planform using dye visualization, Stereoscopic Particle Image Velocimetry (stereo-PIV). The instantaneous images are acquired on the plan-view plane within 5o≤α≤20o to calculate the time-averaged flow data. It can be concluded that vortical flow with a pair of well-defined LEVs over X-45 develop at very low angles of attack, secondary vortex are also evident and form close to the wing surface similar to delta and lambda planforms. The stall occurs at an angle of attack α=32o. <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=delta%20wing" title=" delta wing"> delta wing</a>, <a href="https://publications.waset.org/abstracts/search?q=PIV" title=" PIV"> PIV</a>, <a href="https://publications.waset.org/abstracts/search?q=vortex%20breakdown" title=" vortex breakdown"> vortex breakdown</a> </p> <a href="https://publications.waset.org/abstracts/45231/investigation-of-flow-structure-over-x-45-type-non-slender-delta-wing-planform" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/45231.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">420</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">5917</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">5916</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">5915</span> Determination of Optimum Fin Wave Angle and Its Effect on the Performance of an Intercooler</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Mahdi%20Hamzehei">Mahdi Hamzehei</a>, <a href="https://publications.waset.org/abstracts/search?q=Seyyed%20Amin%20Hakim"> Seyyed Amin Hakim</a>, <a href="https://publications.waset.org/abstracts/search?q=Nahid%20Taherian"> Nahid Taherian</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Fins play an important role in increasing the efficiency of compact shell and tube heat exchangers by increasing heat transfer. The objective of this paper is to determine the optimum fin wave angle, as one of the geometric parameters affecting the efficiency of the heat exchangers. To this end, finite volume method is used to model and simulate the flow in heat exchanger. In this study, computational fluid dynamics simulations of wave channel are done. The results show that the wave angle affects the temperature output of the heat exchanger. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=fin%20wave%20angle" title="fin wave angle">fin wave angle</a>, <a href="https://publications.waset.org/abstracts/search?q=tube" title=" tube"> tube</a>, <a href="https://publications.waset.org/abstracts/search?q=intercooler" title=" intercooler"> intercooler</a>, <a href="https://publications.waset.org/abstracts/search?q=optimum" title=" optimum"> optimum</a>, <a href="https://publications.waset.org/abstracts/search?q=performance" title=" performance"> performance</a> </p> <a href="https://publications.waset.org/abstracts/41621/determination-of-optimum-fin-wave-angle-and-its-effect-on-the-performance-of-an-intercooler" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/41621.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">383</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">5914</span> Power Performance Improvement of 500W Vertical Axis Wind Turbine with Salient Design Parameters</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Young-Tae%20Lee">Young-Tae Lee</a>, <a href="https://publications.waset.org/abstracts/search?q=Hee-Chang%20Lim"> Hee-Chang Lim</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper presents the performance characteristics of Darrieus-type vertical axis wind turbine (VAWT) with NACA airfoil blades. The performance of Darrieus-type VAWT can be characterized by torque and power. There are various parameters affecting the performance such as chord length, helical angle, pitch angle and rotor diameter. To estimate the optimum shape of Darrieustype wind turbine in accordance with various design parameters, we examined aerodynamic characteristics and separated flow occurring in the vicinity of blade, interaction between flow and blade, and torque and power characteristics derived from it. For flow analysis, flow variations were investigated based on the unsteady RANS (Reynolds-averaged Navier-Stokes) equation. Sliding mesh algorithm was employed in order to consider rotational effect of blade. To obtain more realistic results we conducted experiment and numerical analysis at the same time for three-dimensional shape. In addition, several parameters (chord length, rotor diameter, pitch angle, and helical angle) were considered to find out optimum shape design and characteristics of interaction with ambient flow. Since the NACA airfoil used in this study showed significant changes in magnitude of lift and drag depending on an angle of attack, the rotor with low drag, long cord length and short diameter shows high power coefficient in low tip speed ratio (TSR) range. On the contrary, in high TSR range, drag becomes high. Hence, the short-chord and long-diameter rotor produces high power coefficient. When a pitch angle at which airfoil directs toward inside equals to -2° and helical angle equals to 0°, Darrieus-type VAWT generates maximum power. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=darrieus%20wind%20turbine" title="darrieus wind turbine">darrieus wind turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=VAWT" title=" VAWT"> VAWT</a>, <a href="https://publications.waset.org/abstracts/search?q=NACA%20airfoil" title=" NACA airfoil"> NACA airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=performance" title=" performance"> performance</a> </p> <a href="https://publications.waset.org/abstracts/40354/power-performance-improvement-of-500w-vertical-axis-wind-turbine-with-salient-design-parameters" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/40354.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">373</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">5913</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">5912</span> The Influence of Chevron Angle on Plate Heat Exchanger Thermal Performance with Considering Maldistribution</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Hossein%20Shokouhmand">Hossein Shokouhmand</a>, <a href="https://publications.waset.org/abstracts/search?q=Majid%20Hasanpour"> Majid Hasanpour</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A new modification to the Strelow method of chevron-type plate heat exchangers (PHX) modeling is proposed. The effects of maldistribution are accounted in the resulting equation. The results of calculations are validated by reported experiences. The good accuracy of heat transfer performance prediction is shown. The results indicate that considering flow maldistribution improve the accuracy of predicting the flow and thermal behavior of the plate exchanger. Additionally, a wide range of the parametric study has been presented which brings out the effects of chevron angle of PHE on its thermal efficiency with considering maldistribution effect. In addition, the thermally optimal corrugation discussed for the chevron-type PHEs. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=chevron%20angle" title="chevron angle">chevron angle</a>, <a href="https://publications.waset.org/abstracts/search?q=plate%20heat%20exchangers" title=" plate heat exchangers"> plate heat exchangers</a>, <a href="https://publications.waset.org/abstracts/search?q=maldistribution" title=" maldistribution"> maldistribution</a>, <a href="https://publications.waset.org/abstracts/search?q=strelow%20method" title=" strelow method"> strelow method</a> </p> <a href="https://publications.waset.org/abstracts/86320/the-influence-of-chevron-angle-on-plate-heat-exchanger-thermal-performance-with-considering-maldistribution" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/86320.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">5911</span> Investigating the Effects of Thermal and Surface Energy on the Two-Dimensional Flow Characteristics of Oil in Water Mixture between Two Parallel Plates: A Lattice Boltzmann Method Study</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=W.%20Hasan">W. Hasan</a>, <a href="https://publications.waset.org/abstracts/search?q=H.%20Farhat"> H. Farhat</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A hybrid quasi-steady thermal lattice Boltzmann model was used to study the combined effects of temperature and contact angle on the movement of slugs and droplets of oil in water (O/W) system flowing between two parallel plates. The model static contact angle due to the deposition of the O/W droplet on a flat surface with simulated hydrophilic characteristic at different fluid temperatures, matched very well the proposed theoretical calculation. Furthermore, the model was used to simulate the dynamic behavior of droplets and slugs deposited on the domain’s upper and lower surfaces, while subjected to parabolic flow conditions. The model accurately simulated the contact angle hysteresis for the dynamic droplets cases. It was also shown that at elevated temperatures the required power to transport the mixture diminished remarkably. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=lattice%20Boltzmann%20method" title="lattice Boltzmann method">lattice Boltzmann method</a>, <a href="https://publications.waset.org/abstracts/search?q=Gunstensen%20model" title=" Gunstensen model"> Gunstensen model</a>, <a href="https://publications.waset.org/abstracts/search?q=thermal" title=" thermal"> thermal</a>, <a href="https://publications.waset.org/abstracts/search?q=contact%20angle" title=" contact angle"> contact angle</a>, <a href="https://publications.waset.org/abstracts/search?q=high%20viscosity%20ratio" title=" high viscosity ratio"> high viscosity ratio</a> </p> <a href="https://publications.waset.org/abstracts/74061/investigating-the-effects-of-thermal-and-surface-energy-on-the-two-dimensional-flow-characteristics-of-oil-in-water-mixture-between-two-parallel-plates-a-lattice-boltzmann-method-study" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/74061.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">370</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">5910</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">5909</span> Application of Co-Flow Jet Concept to Aircraft Lift Increase</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Sai%20Likitha%20Siddanathi">Sai Likitha Siddanathi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Present project is aimed at increasing the amount of lift produced by typical airfoil. This is achieved by its modification into the co-flow jet structure where a new internal flow is created inside the airfoil from well-designed apertures on its surface. The limit where produced excess lift overcomes the weight of pumping system inserted in airfoil upper portion, and drag force is converted into thrust is discussed in terms of airfoil velocity and angle of attack. Two normal and co-flow jet models are numerically designed and experimental results for both fabricated normal airfoil and CFJ model have been tested in low subsonic wind tunnel. Application has been made to subsonic NACA 652-415 airfoil. Produced lift in CFJ airfoil indicates a maximum value up to a factor of 5 above normal airfoil nearby flow separation ie in relatively weak flow distribution. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=flow%20Jet" title="flow Jet">flow Jet</a>, <a href="https://publications.waset.org/abstracts/search?q=lift%20coefficient" title=" lift coefficient"> lift coefficient</a>, <a href="https://publications.waset.org/abstracts/search?q=drag%20coefficient" title=" drag coefficient"> drag coefficient</a>, <a href="https://publications.waset.org/abstracts/search?q=airfoil%20performance" title=" airfoil performance"> airfoil performance</a> </p> <a href="https://publications.waset.org/abstracts/42591/application-of-co-flow-jet-concept-to-aircraft-lift-increase" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/42591.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">356</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">5908</span> Numerical Investigation of Divergence and Rib Orientation Effects on Thermal Performance in a Divergent Duct, as an Application of Inner Cooling of Turbine Blades</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Heidar%20Jafarizadeh">Heidar Jafarizadeh</a>, <a href="https://publications.waset.org/abstracts/search?q=Hossein%20Keshtkar"> Hossein Keshtkar</a>, <a href="https://publications.waset.org/abstracts/search?q=Ahmad%20Sohankar"> Ahmad Sohankar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Heat transfer and turbulent flow structure have been studied in a divergent ribbed duct with a varying duct geometry with Reynolds numbers of 7000 to 90000 using numerical methods. In this study, we confirmed our numerical results of a ribbed duct with an Initial slope of zero to 3 degree by comparing them to experimental data we had and investigated the impact of the ducts divergence on heat transfer and flow pattern in the 2-dimensional flow. Then we investigated the effect of tilting the ribs, on heat transfer and flow behavior. We achieved this by changing the ribs angles from a range of 40 to 75 degrees in a divergent duct and simulated the flow in 3-dimensions. Our results show that with an increase in duct divergence, heat transfer increases linearly and the coefficient of friction increases exponentially. As the results show, a duct with a divergence angle of 1.5 degree presents better thermal performance in comparison with all the angle range’s we studied. Besides, a ribbed duct with 40 degree rib orientation had the best thermal performance considering the simultaneous effects of pressure drop and heat transfer which were imposed on it. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=divergent%20ribbed%20duct" title="divergent ribbed duct">divergent ribbed duct</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=thermal%20performance" title=" thermal performance"> thermal performance</a>, <a href="https://publications.waset.org/abstracts/search?q=turbulent%20flow%20structure" title=" turbulent flow structure"> turbulent flow structure</a> </p> <a href="https://publications.waset.org/abstracts/74676/numerical-investigation-of-divergence-and-rib-orientation-effects-on-thermal-performance-in-a-divergent-duct-as-an-application-of-inner-cooling-of-turbine-blades" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/74676.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">302</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">5907</span> Prediction of Trailing-Edge Noise under Adverse-Pressure Gradient Effect</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Li%20Chen">Li Chen</a> </p> <p class="card-text"><strong>Abstract:</strong></p> For an aerofoil or hydrofoil in high Reynolds number flows, broadband noise is generated efficiently as the result of the turbulence convecting over the trailing edge. This noise can be related to the surface pressure fluctuations, which can be predicted by either CFD or empirical models. However, in reality, the aerofoil or hydrofoil often operates at an angle of attack. Under this situation, the flow is subjected to an Adverse-Pressure-Gradient (APG), and as a result, a flow separation may occur. This study is to assess trailing-edge noise models for such flows. In the present work, the trailing-edge noise from a 2D airfoil at 6 degree of angle of attach is investigated. Under this condition, the flow is experiencing a strong APG, and the flow separation occurs. The flow over the airfoil with a chord of 300 mm, equivalent to a Reynold Number 4x10⁵, is simulated using RANS with the SST k-ɛ turbulent model. The predicted surface pressure fluctuations are compared with the published experimental data and empirical models, and show a good agreement with the experimental data. The effect of the APG on the trailing edge noise is discussed, and the associated trailing edge noise is calculated. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aero-acoustics" title="aero-acoustics">aero-acoustics</a>, <a href="https://publications.waset.org/abstracts/search?q=adverse-pressure%20gradient" title=" adverse-pressure gradient"> adverse-pressure gradient</a>, <a href="https://publications.waset.org/abstracts/search?q=computational%20fluid%20dynamics" title=" computational fluid dynamics"> computational fluid dynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=trailing-edge%20noise" title=" trailing-edge noise"> trailing-edge noise</a> </p> <a href="https://publications.waset.org/abstracts/65472/prediction-of-trailing-edge-noise-under-adverse-pressure-gradient-effect" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/65472.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">336</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">5906</span> Performance of a Sailing Vessel with a Solid Wing Sail Compared to a Traditional Sail</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=William%20Waddington">William Waddington</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20Jahir%20Rizvi"> M. Jahir Rizvi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Sail used to propel a vessel functions in a similar way to an aircraft wing. Traditionally, cloth and ropes were used to produce sails. However, there is one major problem with traditional sail design, the increase in turbulence and flow separation when compared to that of an aircraft wing with the same camber. This has led to the development of the solid wing sail focusing mainly on the sail shape. Traditional cloth sails are manufactured as a single element whereas solid wing sail is made of two segments. To the authors’ best knowledge, the phenomena behind the performances of this type of sail at various angles of wind direction with respect to a sailing vessel’s direction (known as the angle of attack) is still an area of mystery. Hence, in this study, the thrusts of a sailing vessel produced by wing sails constructed with various angles (22°, 24°, 26° and 28°) between the two segments have been compared to that of a traditional cloth sail made of carbon-fiber material. The reason for using carbon-fiber material is to achieve the correct and the exact shape of a commercially available mainsail. NACA 0024 and NACA 0016 foils have been used to generate two-segment wing sail shape which incorporates a flap between the first and the second segments. Both the two-dimensional and the three-dimensional sail models designed in commercial CAD software Solidworks have been analyzed through Computational Fluid Dynamics (CFD) techniques using Ansys CFX considering an apparent wind speed of 20.55 knots with an apparent wind angle of 31°. The results indicate that the thrust from traditional sail increases from 8.18 N to 8.26 N when the angle of attack is increased from 5° to 7°. However, the thrust value decreases if the angle of attack is further increased. A solid wing sail which possesses 20° angle between its two segments, produces thrusts from 7.61 N to 7.74 N with an increase in the angle of attack from 7° to 8°. The thrust remains steady up to 9° angle of attack and drops dramatically beyond 9°. The highest thrust values that can be obtained for the solid wing sails with 22°, 24°, 26° and 28° angle respectively between the two segments are 8.75 N, 9.10 N, 9.29 N and 9.19 N respectively. The optimum angle of attack for each of the solid wing sails is identified as 7° at which these thrust values are obtained. Therefore, it can be concluded that all the thrust values predicted for the solid wing sails of angles between the two segments above 20° are higher compared to the thrust predicted for the traditional sail. However, the best performance from a solid wing sail is expected when the sail is created with an angle between the two segments above 20° but below or equal to 26°. In addition, 1/29th scale models in the wind tunnel have been tested to observe the flow behaviors around the sails. The experimental results support the numerical observations as the flow behaviors are exactly the same. <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=drag" title=" drag"> drag</a>, <a href="https://publications.waset.org/abstracts/search?q=sailing%20vessel" title=" sailing vessel"> sailing vessel</a>, <a href="https://publications.waset.org/abstracts/search?q=thrust" title=" thrust"> thrust</a>, <a href="https://publications.waset.org/abstracts/search?q=traditional%20sail" title=" traditional sail"> traditional sail</a>, <a href="https://publications.waset.org/abstracts/search?q=wing%20sail" title=" wing sail"> wing sail</a> </p> <a href="https://publications.waset.org/abstracts/93023/performance-of-a-sailing-vessel-with-a-solid-wing-sail-compared-to-a-traditional-sail" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/93023.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">279</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">5905</span> Diagnostic Investigation of Aircraft Performance at Different Winglet Cant Angles </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=M.%20Dinesh">M. Dinesh</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20Kenny%20Mark"> V. Kenny Mark</a>, <a href="https://publications.waset.org/abstracts/search?q=Dharni%20Vasudhevan%20Venkatesan"> Dharni Vasudhevan Venkatesan</a>, <a href="https://publications.waset.org/abstracts/search?q=B.%20Santhosh%20Kumar"> B. Santhosh Kumar</a>, <a href="https://publications.waset.org/abstracts/search?q=R.%20Sree%20Radesh"> R. Sree Radesh</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20R.%20Sanal%20Kumar"> V. R. Sanal Kumar </a> </p> <p class="card-text"><strong>Abstract:</strong></p> Comprehensive numerical studies have been carried out to examine the best aerodynamic performance of subsonic aircraft at different winglet cant angles using a validated 3D k-ω SST model. In the parametric analytical studies, NACA series of airfoils are selected. Basic design of the winglet is selected from the literature and flow features of the entire wing including the winglet tip effects have been examined with different cant angles varying from 150 to 600 at different angles of attack up to 140. We have observed, among the cases considered in this study that a case with 150 cant angle the aerodynamics performance of the subsonic aircraft during takeoff was found better up to an angle of attack of 2.80 and further its performance got diminished at higher angles of attack. Analyses further revealed that increasing the winglet cant angle from 150 to 600 at higher angles of attack could negate the performance deterioration and additionally it could enhance the peak CL/CD on the order of 3.5%. The investigated concept of variable-cant-angle winglets appears to be a promising alternative for improving the aerodynamic efficiency of aircraft. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20efficiency" title="aerodynamic efficiency">aerodynamic efficiency</a>, <a href="https://publications.waset.org/abstracts/search?q=cant%20angle" title=" cant angle"> cant angle</a>, <a href="https://publications.waset.org/abstracts/search?q=drag%20reduction" title=" drag reduction"> drag reduction</a>, <a href="https://publications.waset.org/abstracts/search?q=flexible%20winglets" title=" flexible winglets "> flexible winglets </a> </p> <a href="https://publications.waset.org/abstracts/18421/diagnostic-investigation-of-aircraft-performance-at-different-winglet-cant-angles" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/18421.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">523</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">5904</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">5903</span> Numerical Predictions of Trajectory Stability of a High-Speed Water-Entry and Water-Exit Projectile </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Lin%20Lu">Lin Lu</a>, <a href="https://publications.waset.org/abstracts/search?q=Qiang%20Li"> Qiang Li</a>, <a href="https://publications.waset.org/abstracts/search?q=Tao%20Cai"> Tao Cai</a>, <a href="https://publications.waset.org/abstracts/search?q=Pengjun%20Zhang"> Pengjun Zhang</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this study, a detailed analysis of trajectory stability and flow characteristics of a high-speed projectile during the water-entry and water-exit process has been investigated numerically. The Zwart-Gerber-Belamri (Z-G-B) cavitation model and the SST k-ω turbulence model based on the Reynolds Averaged Navier-Stokes (RANS) method are employed. The numerical methodology is validated by comparing the experimental photograph of cavitation shape and the experimental underwater velocity with the numerical simulation results. Based on the numerical methodology, the influences of rotational speed, water-entry and water-exit angle of the projectile on the trajectory stability and flow characteristics have been carried out in detail. The variation features of projectile trajectory and total resistance have been conducted, respectively. In addition, the cavitation characteristics of water-entry and water-exit have been presented and analyzed. Results show that it may not be applicable for the water-entry and water-exit to achieve the projectile stability through the rotation of projectile. Furthermore, there ought to be a critical water-entry angle for the water-entry stability of practical projectile. The impact of water-exit angle on the trajectory stability and cavity phenomenon is not as remarkable as that of the water-entry angle. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=cavitation%20characteristics" title="cavitation characteristics">cavitation characteristics</a>, <a href="https://publications.waset.org/abstracts/search?q=high-speed%20projectile" title=" high-speed projectile"> high-speed projectile</a>, <a href="https://publications.waset.org/abstracts/search?q=numerical%20predictions" title=" numerical predictions"> numerical predictions</a>, <a href="https://publications.waset.org/abstracts/search?q=trajectory%20stability" title=" trajectory stability"> trajectory stability</a>, <a href="https://publications.waset.org/abstracts/search?q=water-entry" title=" water-entry"> water-entry</a>, <a href="https://publications.waset.org/abstracts/search?q=water-exit" title=" water-exit"> water-exit</a> </p> <a href="https://publications.waset.org/abstracts/119865/numerical-predictions-of-trajectory-stability-of-a-high-speed-water-entry-and-water-exit-projectile" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/119865.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">136</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=flow%20angle&page=2">2</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=flow%20angle&page=3">3</a></li> <li class="page-item"><a class="page-link" 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