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airfoil</title> <meta name="description" content="Search results for: dihedral airfoil"> <meta name="keywords" content="dihedral airfoil"> <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 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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="dihedral airfoil"> <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> 115</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: dihedral airfoil</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">115</span> Supersonic Flow around a Dihedral Airfoil: Modeling and Experimentation Investigation</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=A.%20Naamane">A. Naamane</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20Hasnaoui"> M. Hasnaoui</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Numerical modeling of fluid flows, whether compressible or incompressible, laminar or turbulent presents a considerable contribution in the scientific and industrial fields. However, the development of an approximate model of a supersonic flow requires the introduction of specific and more precise techniques and methods. For this purpose, the object of this paper is modeling a supersonic flow of inviscid fluid around a dihedral airfoil. Based on the thin airfoils theory and the non-dimensional stationary Steichen equation of a two-dimensional supersonic flow in isentropic evolution, we obtained a solution for the downstream velocity potential of the oblique shock at the second order of relative thickness that characterizes a perturbation parameter. This result has been dealt with by the asymptotic analysis and characteristics method. In order to validate our model, the results are discussed in comparison with theoretical and experimental results. Indeed, firstly, the comparison of the results of our model has shown that they are quantitatively acceptable compared to the existing theoretical results. Finally, an experimental study was conducted using the AF300 supersonic wind tunnel. In this experiment, we have considered the incident upstream Mach number over a symmetrical dihedral airfoil wing. The comparison of the different Mach number downstream results of our model with those of the existing theoretical data (relative margin between 0.07% and 4%) and with experimental results (concordance for a deflection angle between 1° and 11°) support the validation of our model with accuracy. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=asymptotic%20modelling" title="asymptotic modelling">asymptotic modelling</a>, <a href="https://publications.waset.org/abstracts/search?q=dihedral%20airfoil" title=" dihedral airfoil"> dihedral airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=supersonic%20flow" title=" supersonic flow"> supersonic flow</a>, <a href="https://publications.waset.org/abstracts/search?q=supersonic%20wind%20tunnel" title=" supersonic wind tunnel"> supersonic wind tunnel</a> </p> <a href="https://publications.waset.org/abstracts/104317/supersonic-flow-around-a-dihedral-airfoil-modeling-and-experimentation-investigation" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/104317.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">134</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">114</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">113</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">112</span> Experimental Investigation on Noise from Rod-Airfoil with Leading Edge Serrations</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Siti%20Ruhliah%20Lizarose%20Samion">Siti Ruhliah Lizarose Samion</a>, <a href="https://publications.waset.org/abstracts/search?q=Mohamed%20Sukri%20Mat%20Ali"> Mohamed Sukri Mat Ali</a>, <a href="https://publications.waset.org/abstracts/search?q=Con%20Doolan"> Con Doolan</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The present work is an experimental investigation of adapting a passive treatment leading edge serrations over a rod-airfoil flow-induced noise generation. The leading edge serrations are bio-inspired from a barn-owl silent flight. The rod-airfoil configuration is a benchmark configuration taken to investigate airfoil-turbulence interaction noise (ATIN). Location of serrations placed and the wideness of serrations are the two parameters taken in this study. The ATIN is reduced up to 3.5 dB for a wide leading serrations case. A correlation is found between the wideness of serrations and the noise reduction mechanism of the airfoil. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20noise" title="aerodynamic noise">aerodynamic noise</a>, <a href="https://publications.waset.org/abstracts/search?q=leading%20edge%20serrations" title=" leading edge serrations"> leading edge serrations</a>, <a href="https://publications.waset.org/abstracts/search?q=rod-airfoil" title=" rod-airfoil"> rod-airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=experiment" title=" experiment"> experiment</a> </p> <a href="https://publications.waset.org/abstracts/84951/experimental-investigation-on-noise-from-rod-airfoil-with-leading-edge-serrations" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/84951.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">353</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">111</span> Towards a Biologically Inspired Supercritical Airfoil Adapted for Gliding Cross-Domain Vehicles</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Hanyue%20Shen">Hanyue Shen</a>, <a href="https://publications.waset.org/abstracts/search?q=Jiaying%20Zhang"> Jiaying Zhang</a>, <a href="https://publications.waset.org/abstracts/search?q=Xingwei%20Kong"> Xingwei Kong</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Growing research on cross-domain vehicles (CDVs) has addressed the requirement to balance airfoil efficiency in air and water. No existing airfoil is specifically developed to adapt to the large Reynold’s number range CDVs operate in. This research proposes a supercritical airfoil biologically inspired by Atlantic Puffins. The initial airfoil is parameterized with the composite Karman-Trefftz method, optimized with a series of multi-stage gradient descend procedures, and compared with other airfoils with Xfoil. Results from Xfoil are also validated via Fluent and experiment considering curvatures on the designed airfoil might affect the accuracy of Xfoil. The results indicate that while CFD and Xfoil results closely align, Xfoil produces results closest to the experimental value. The bionic airfoil demonstrates superior performance in the range Re = 2·10⁴ to Re = 2·10⁵ compared to other studied airfoils, satisfying design requirements. This airfoil and its future counterparts are probable solutions to be implemented on fixed-wing CDVs desiring to glide in the given working conditions, providing an efficient and structurally simple pathway. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=fluid%20dynamics" title="fluid dynamics">fluid dynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=airfoil%20design" title=" airfoil design"> airfoil design</a>, <a href="https://publications.waset.org/abstracts/search?q=biomimicry" title=" biomimicry"> biomimicry</a>, <a href="https://publications.waset.org/abstracts/search?q=cross%20domain%20vehicle" title=" cross domain vehicle"> cross domain vehicle</a> </p> <a href="https://publications.waset.org/abstracts/191250/towards-a-biologically-inspired-supercritical-airfoil-adapted-for-gliding-cross-domain-vehicles" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/191250.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">51</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">110</span> The Influence of Variable Geometrical Modifications of the Trailing Edge of Supercritical Airfoil on the Characteristics of Aerodynamics</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=P.%20Lauk">P. Lauk</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20E.%20Seegel"> K. E. Seegel</a>, <a href="https://publications.waset.org/abstracts/search?q=T.%20T%C3%A4hemaa"> T. Tähemaa</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The fuel consumption of modern, high wing loading, commercial aircraft in the first stage of flight is high because the usable flight level is lower and the weather conditions (jet stream) have great impact on aircraft performance. To reduce the fuel consumption, it is necessary to raise during first stage of flight the L/D ratio value within Cl 0.55-0.65. Different variable geometrical wing trailing edge modifications of SC(2)-410 airfoil were compared at M 0.78 using the CFD software STAR-CCM+ simulation based Reynolds-averaged Navier-Stokes (RANS) equations. The numerical results obtained show that by increasing the width of the airfoil by 4% and by modifying the trailing edge airfoil, it is possible to decrease airfoil drag at Cl 0.70 for up to 26.6% and at the same time to increase commercial aircraft L/D ratio for up to 5.0%. Fuel consumption can be reduced in proportion to the increase in L/D ratio. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=L%2FD%20ratio" title="L/D ratio">L/D ratio</a>, <a href="https://publications.waset.org/abstracts/search?q=miniflaps" title=" miniflaps"> miniflaps</a>, <a href="https://publications.waset.org/abstracts/search?q=mini-TED" title=" mini-TED"> mini-TED</a>, <a href="https://publications.waset.org/abstracts/search?q=supercritical%20airfoil" title=" supercritical airfoil"> supercritical airfoil</a> </p> <a href="https://publications.waset.org/abstracts/85202/the-influence-of-variable-geometrical-modifications-of-the-trailing-edge-of-supercritical-airfoil-on-the-characteristics-of-aerodynamics" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/85202.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">207</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">109</span> Surface Pressure Distribution of a Flapped-Airfoil for Different Momentum Injection at the Leading Edge</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Mohammad%20Mashud">Mohammad Mashud</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20M.%20Nahid%20Hasan"> S. M. Nahid Hasan</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The aim of the research work is to modify the NACA 4215 airfoil with flap and rotary cylinder at the leading edge of the airfoil and experimentally study the static pressure distribution over the airfoil completed with flap and leading-edge vortex generator. In this research, NACA 4215 wing model has been constructed by generating the profile geometry using the standard equations and design software such as AutoCAD and SolidWorks. To perform the experiment, three wooden models are prepared and tested in subsonic wind tunnel. The experiments were carried out in various angles of attack. Flap angle and momentum injection rate are changed to observe the characteristics of pressure distribution. In this research, a new concept of flow separation control mechanism has been introduced to improve the aerodynamic characteristics of airfoil. Control of flow separation over airfoil which experiences a vortex generator (rotating cylinder) at the leading edge of airfoil is experimentally simulated under the effects of momentum injection. The experimental results show that the flow separation control is possible by the proposed mechanism, and benefits can be achieved by momentum injection technique. The wing performance is significantly improved due to control of flow separation by momentum injection method. <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=momentum%20injection" title=" momentum injection"> momentum injection</a>, <a href="https://publications.waset.org/abstracts/search?q=flap" title=" flap"> flap</a>, <a href="https://publications.waset.org/abstracts/search?q=pressure%20distribution" title=" pressure distribution"> pressure distribution</a> </p> <a href="https://publications.waset.org/abstracts/106872/surface-pressure-distribution-of-a-flapped-airfoil-for-different-momentum-injection-at-the-leading-edge" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/106872.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">140</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">108</span> Variation of Airfoil Pressure Profile Due to Confined Air Streams: Application in Gas-Oil Separators</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Amir%20Hossein%20Haji">Amir Hossein Haji</a>, <a href="https://publications.waset.org/abstracts/search?q=Nabeel%20Al-Rawahi"> Nabeel Al-Rawahi</a>, <a href="https://publications.waset.org/abstracts/search?q=Gholamreza%20Vakili-Nezhaad"> Gholamreza Vakili-Nezhaad</a> </p> <p class="card-text"><strong>Abstract:</strong></p> An innovative design has been examined for a gas-oil separator based on pressure reduction over an airfoil surface. The primary motivations are to shorten the release trajectory of the bubbles by minimizing the thickness of the oil layer as well as improving uniform pressure reduction zones. Restricted airflow over an airfoil is investigated for its effect on the pressure drop enhancement and the maximum attainable attack angle prior to the stall condition. Aerodynamic separation is delayed based on numerical simulation of Wortmann FX 63137 Airfoil in a confined domain using FLUENT 6.3.26. The proposed set up results in higher pressure drop compared with the free stream case. With the aim of optimum power consumption we have pursued further restriction to an air jet case over the airfoil. Then, a curved strip model is suggested for the air jet which can be applied as an analysis/design tool for the best performance conditions. Pressure reduction is shown to be inversely proportional to the curvature of the upper airfoil profile. This reduction occurs within the tracking zones where the air jet is effectively attached to the airfoil surface. The zero slope condition is suggested to estimate the onset of these zones after which the minimum curvature should be searched. The corresponding zero slope curvature is applied for estimation of the maximum pressure drop which shows satisfactory agreement with the simulation results. <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=air%20jet" title=" air jet"> air jet</a>, <a href="https://publications.waset.org/abstracts/search?q=curved%20fluid%20flow" title=" curved fluid flow"> curved fluid flow</a>, <a href="https://publications.waset.org/abstracts/search?q=gas-oil%20separator" title=" gas-oil separator"> gas-oil separator</a> </p> <a href="https://publications.waset.org/abstracts/1375/variation-of-airfoil-pressure-profile-due-to-confined-air-streams-application-in-gas-oil-separators" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/1375.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">473</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">107</span> Comparative Analysis of High Lift Airfoils for Motorsports Applications</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=M.%20Fozan%20Ur%20Rab">M. Fozan Ur Rab</a>, <a href="https://publications.waset.org/abstracts/search?q=Mahrukh"> Mahrukh</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20Alam"> M. Alam</a>, <a href="https://publications.waset.org/abstracts/search?q=N.%20Sheikh"> N. Sheikh</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The purpose of this study is to analyze various high lift low Reynolds number airfoils using two-dimensional Computational Fluid Dynamics (CFD) code in the isolated flow field and select optimum airfoil to suit the motorsports application. The airfoil is selected after comparing the stall behavior, transition location, pressure recovery, pressure distribution and boundary layer characteristics of various airfoils. The prime consideration while selecting airfoil is highest Cl while achieving the sustainable performance over a range of Reynolds numbers encountered on the race track. The increase in Cl is always accompanied by the increase in Cd but this must be compromised since the main goal is to increase an aerodynamic grip. It is always desirable to increase the down-force in Formula One (F1)/Formula Student (FS) to gain reduction in lap time. This paper establishes the criteria for selection of high lift low Reynolds number airfoil while considering various parameters which affect the performance of airfoils. <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=airfoil" title=" airfoil"> airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=downforce" title=" downforce"> downforce</a>, <a href="https://publications.waset.org/abstracts/search?q=formula%20student" title=" formula student"> formula student</a>, <a href="https://publications.waset.org/abstracts/search?q=lap%20time" title=" lap time"> lap time</a> </p> <a href="https://publications.waset.org/abstracts/93779/comparative-analysis-of-high-lift-airfoils-for-motorsports-applications" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/93779.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">288</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">106</span> Effect of Synthetic Jet on Wind Turbine Noise</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Reda%20Mankbadi">Reda Mankbadi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The current work explores the use of Synthetic Jet Actuators (SJAs) for control of the acoustic radiation of a low-speed transitioning airfoil in a uniform stream. In the adopted numerical procedure, the actuator is modeled without its resonator cavity through imposing a simple fluctuating-velocity boundary condition at the bottom of the actuator's orifice. The orifice cavity, with the properly defined boundary condition, is then embedded into the airfoil surface. High-accuracy viscous simulations are then conducted to study the effects of the actuation on sound radiated by the airfoil. Results show that SJA can considerably suppress the radiated sound of the airfoil in uniform incoming stream. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=simulations" title="simulations">simulations</a>, <a href="https://publications.waset.org/abstracts/search?q=aeroacoustics" title=" aeroacoustics"> aeroacoustics</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20turbine%20noise" title=" wind turbine noise"> wind turbine noise</a>, <a href="https://publications.waset.org/abstracts/search?q=synthetic%20jet%20actuators%20%28SJAs%29" title=" synthetic jet actuators (SJAs)"> synthetic jet actuators (SJAs)</a> </p> <a href="https://publications.waset.org/abstracts/28530/effect-of-synthetic-jet-on-wind-turbine-noise" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/28530.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">105</span> Effect of Mach Number for Gust-Airfoil Interatcion Noise</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=ShuJiang%20Jiang">ShuJiang Jiang</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The interaction of turbulence with airfoil is an important noise source in many engineering fields, including helicopters, turbofan, and contra-rotating open rotor engines, where turbulence generated in the wake of upstream blades interacts with the leading edge of downstream blades and produces aerodynamic noise. One approach to study turbulence-airfoil interaction noise is to model the oncoming turbulence as harmonic gusts. A compact noise source produces a dipole-like sound directivity pattern. However, when the acoustic wavelength is much smaller than the airfoil chord length, the airfoil needs to be treated as a non-compact source, and the gust-airfoil interaction becomes more complicated and results in multiple lobes generated in the radiated sound directivity. Capturing the short acoustic wavelength is a challenge for numerical simulations. In this work, simulations are performed for gust-airfoil interaction at different Mach numbers, using a high-fidelity direct Computational AeroAcoustic (CAA) approach based on a spectral/hp element method, verified by a CAA benchmark case. It is found that the squared sound pressure varies approximately as the 5th power of Mach number, which changes slightly with the observer location. This scaling law can give a better sound prediction than the flat-plate theory for thicker airfoils. Besides, another prediction method, based on the flat-plate theory and CAA simulation, has been proposed to give better predictions than the scaling law for thicker airfoils. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aeroacoustics" title="aeroacoustics">aeroacoustics</a>, <a href="https://publications.waset.org/abstracts/search?q=gust-airfoil%20interaction" title=" gust-airfoil interaction"> gust-airfoil interaction</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=CAA" title=" CAA"> CAA</a> </p> <a href="https://publications.waset.org/abstracts/168371/effect-of-mach-number-for-gust-airfoil-interatcion-noise" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/168371.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">78</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">104</span> Numerical Investigation of Dynamic Stall over a Wind Turbine Pitching Airfoil by Using OpenFOAM</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Mahbod%20Seyednia">Mahbod Seyednia</a>, <a href="https://publications.waset.org/abstracts/search?q=Shidvash%20Vakilipour"> Shidvash Vakilipour</a>, <a href="https://publications.waset.org/abstracts/search?q=Mehran%20Masdari"> Mehran Masdari</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Computations for two-dimensional flow past a stationary and harmonically pitching wind turbine airfoil at a moderate value of Reynolds number (400000) are carried out by progressively increasing the angle of attack for stationary airfoil and at fixed pitching frequencies for rotary one. The incompressible Navier-Stokes equations in conjunction with Unsteady Reynolds Average Navier-Stokes (URANS) equations for turbulence modeling are solved by OpenFOAM package to investigate the aerodynamic phenomena occurred at stationary and pitching conditions on a NACA 6-series wind turbine airfoil. The aim of this study is to enhance the accuracy of numerical simulation in predicting the aerodynamic behavior of an oscillating airfoil in OpenFOAM. Hence, for turbulence modelling, <em>k-ω-SST</em> with low-Reynolds correction is employed to capture the unsteady phenomena occurred in stationary and oscillating motion of the airfoil. Using aerodynamic and pressure coefficients along with flow patterns, the unsteady aerodynamics at pre-, near-, and post-static stall regions are analyzed in harmonically pitching airfoil, and the results are validated with the corresponding experimental data possessed by the authors. The results indicate that implementing the mentioned turbulence model leads to accurate prediction of the angle of static stall for stationary airfoil and flow separation, dynamic stall phenomenon, and reattachment of the flow on the surface of airfoil for pitching one. Due to the geometry of the studied 6-series airfoil, the vortex on the upper surface of the airfoil during upstrokes is formed at the trailing edge. Therefore, the pattern flow obtained by our numerical simulations represents the formation and change of the trailing-edge vortex at near- and post-stall regions where this process determines the dynamic stall phenomenon. <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=moderate%20Reynolds%20number" title=" moderate Reynolds number"> moderate Reynolds number</a>, <a href="https://publications.waset.org/abstracts/search?q=OpenFOAM" title=" OpenFOAM"> OpenFOAM</a>, <a href="https://publications.waset.org/abstracts/search?q=pitching%20oscillation" title=" pitching oscillation"> pitching oscillation</a>, <a href="https://publications.waset.org/abstracts/search?q=unsteady%20aerodynamics" title=" unsteady aerodynamics"> unsteady aerodynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20turbine" title=" wind turbine"> wind turbine</a> </p> <a href="https://publications.waset.org/abstracts/76029/numerical-investigation-of-dynamic-stall-over-a-wind-turbine-pitching-airfoil-by-using-openfoam" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/76029.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">203</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">103</span> Numerical Investigations on Dynamic Stall of a Pitching-Plunging Helicopter Blade Airfoil </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Xie%20Kai">Xie Kai</a>, <a href="https://publications.waset.org/abstracts/search?q=Laith%20K.%20Abbas"> Laith K. Abbas</a>, <a href="https://publications.waset.org/abstracts/search?q=Chen%20Dongyang"> Chen Dongyang</a>, <a href="https://publications.waset.org/abstracts/search?q=Yang%20Fufeng"> Yang Fufeng</a>, <a href="https://publications.waset.org/abstracts/search?q=Rui%20Xiaoting"> Rui Xiaoting</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Effect of plunging motion on the pitch oscillating NACA0012 airfoil is investigated using computational fluid dynamics (CFD). A simulation model based on overset grid technology and <em>k - ω</em> shear stress transport (SST) turbulence model is established, and the numerical simulation results are compared with available experimental data and other simulations. Two cases of phase angle <em>φ = 0, μ </em>which represents the phase difference between the pitching and plunging motions of an airfoil are performed. Airfoil vortex generation, moving, and shedding are discussed in detail. Good agreements have been achieved with the available literature. The upward plunging motion made the equivalent angle of attack less than the actual one during pitching analysis. It is observed that the formation of the stall vortex is suppressed, resulting in a decrease in the lift coefficient and a delay of the stall angle. However, the downward plunging motion made the equivalent angle of attack higher the actual one. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=dynamic%20stall" title="dynamic stall">dynamic stall</a>, <a href="https://publications.waset.org/abstracts/search?q=pitching-plunging" title=" pitching-plunging"> pitching-plunging</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=helicopter%20blade%20rotor" title=" helicopter blade rotor"> helicopter blade rotor</a>, <a href="https://publications.waset.org/abstracts/search?q=airfoil" title=" airfoil"> airfoil</a> </p> <a href="https://publications.waset.org/abstracts/75693/numerical-investigations-on-dynamic-stall-of-a-pitching-plunging-helicopter-blade-airfoil" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/75693.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">226</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">102</span> Resolution and Experimental Validation of the Asymptotic Model of a Viscous Laminar Supersonic Flow around a Thin Airfoil</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Eddegdag%20Nasser">Eddegdag Nasser</a>, <a href="https://publications.waset.org/abstracts/search?q=Naamane%20Azzeddine"> Naamane Azzeddine</a>, <a href="https://publications.waset.org/abstracts/search?q=Radouani%20Mohammed"> Radouani Mohammed</a>, <a href="https://publications.waset.org/abstracts/search?q=Ensam%20Meknes"> Ensam Meknes</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this study, we are interested in the asymptotic modeling of the two-dimensional stationary supersonic flow of a viscous compressible fluid around wing airfoil. The aim of this article is to solve the partial differential equations of the flow far from the leading edge and near the wall using the triple-deck technique is what brought again in precision according to the principle of least degeneration. In order to validate our theoretical model, these obtained results will be compared with the experimental results. The comparison of the results of our model with experimentation has shown that they are quantitatively acceptable compared to the obtained experimental results. The experimental study was conducted using the AF300 supersonic wind tunnel and a NACA Reduced airfoil model with two pressure Taps on extrados. In this experiment, we have considered the incident upstream supersonic Mach number over a dissymmetric NACA airfoil wing. The validation and the accuracy of the results support our model. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=supersonic" title="supersonic">supersonic</a>, <a href="https://publications.waset.org/abstracts/search?q=viscous" title=" viscous"> viscous</a>, <a href="https://publications.waset.org/abstracts/search?q=triple%20deck%20technique" title=" triple deck technique"> triple deck technique</a>, <a href="https://publications.waset.org/abstracts/search?q=asymptotic%20methods" title=" asymptotic methods"> asymptotic methods</a>, <a href="https://publications.waset.org/abstracts/search?q=AF300%20supersonic%20wind%20tunnel" title=" AF300 supersonic wind tunnel"> AF300 supersonic wind tunnel</a>, <a href="https://publications.waset.org/abstracts/search?q=reduced%20airfoil%20model" title=" reduced airfoil model"> reduced airfoil model</a> </p> <a href="https://publications.waset.org/abstracts/141179/resolution-and-experimental-validation-of-the-asymptotic-model-of-a-viscous-laminar-supersonic-flow-around-a-thin-airfoil" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/141179.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">240</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">101</span> Aerodynamic Analysis of Dimple Effect on Aircraft Wing</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=E.%20Livya">E. Livya</a>, <a href="https://publications.waset.org/abstracts/search?q=G.%20Anitha"> G. Anitha</a>, <a href="https://publications.waset.org/abstracts/search?q=P.%20Valli"> P. Valli</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The main objective of aircraft aerodynamics is to enhance the aerodynamic characteristics and maneuverability of the aircraft. This enhancement includes the reduction in drag and stall phenomenon. The airfoil which contains dimples will have comparatively less drag than the plain airfoil. Introducing dimples on the aircraft wing will create turbulence by creating vortices which delays the boundary layer separation resulting in decrease of pressure drag and also increase in the angle of stall. In addition, wake reduction leads to reduction in acoustic emission. The overall objective of this paper is to improve the aircraft maneuverability by delaying the flow separation point at stall and thereby reducing the drag by applying the dimple effect over the aircraft wing. This project includes both computational and experimental analysis of dimple effect on aircraft wing, using NACA 0018 airfoil. Dimple shapes of Semi-sphere, hexagon, cylinder, square are selected for the analysis; airfoil is tested under the inlet velocity of 30m/s at different angle of attack (5˚, 10˚, 15˚, 20˚, and 25˚). This analysis favours the dimple effect by increasing L/D ratio and thereby providing the maximum aerodynamic efficiency, which provides the enhanced performance for the aircraft. <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=dimple%20effect" title=" dimple effect"> dimple effect</a>, <a href="https://publications.waset.org/abstracts/search?q=turbulence" title=" turbulence"> turbulence</a>, <a href="https://publications.waset.org/abstracts/search?q=boundary%20layer%20separation" title=" boundary layer separation"> boundary layer separation</a> </p> <a href="https://publications.waset.org/abstracts/24631/aerodynamic-analysis-of-dimple-effect-on-aircraft-wing" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/24631.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">533</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">100</span> Numerical Simulation of the Effect of Single and Dual Synthetic Jet on Stall Phenomenon On NACA (National Advisory Committee for Aeronautics) GA(W)-2 Airfoil</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Abbasali%20Abouei%20Mehrizi">Abbasali Abouei Mehrizi</a>, <a href="https://publications.waset.org/abstracts/search?q=Hamid%20Hassanzadeh%20Afrouzi"> Hamid Hassanzadeh Afrouzi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Reducing the drag force increases the efficiency of the aircraft and its better performance. Flow control methods delay the phenomenon of flow separation and consequently reduce the reversed flow phenomenon in the separation region and enhance the performance of the lift force while decreasing the drag force and thus improving the aircraft efficiency. Flow control methods can be divided into active and passive types. The use of synthetic jets actuator (SJA) used in this study for NACA GA (W) -2 airfoil is one of the active flow control methods to prevent stall phenomenon on the airfoil. In this research, the relevant airfoil in different angles of attack with and without jets has been compared by OpenFOAM. Also, after achieving the proper SJA position on the airfoil suction surface, the simultaneous effect of two SJAs has been discussed. It was found to have the best effect at 12% chord (C), close to the airfoil’s leading edge (LE). At 12% chord, SJA decreases the drag significantly with increasing lift, and also, the average lift increase was higher than other situations and was equal to 10.4%. The highest drag reduction was about 5% in SJA=0.25C. Then, due to the positive effects of SJA in the 12% and 25% chord regions, these regions were considered for applying dual jets in two post-stall angles of attack, i.e., 16° and 22°. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=active%20and%20passive%20flow%20control%20methods" title="active and passive flow control methods">active and passive flow control methods</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=flow%20separation" title=" flow separation"> flow separation</a>, <a href="https://publications.waset.org/abstracts/search?q=synthetic%20jet" title=" synthetic jet"> synthetic jet</a> </p> <a href="https://publications.waset.org/abstracts/163363/numerical-simulation-of-the-effect-of-single-and-dual-synthetic-jet-on-stall-phenomenon-on-naca-national-advisory-committee-for-aeronautics-gaw-2-airfoil" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/163363.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">83</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">99</span> Analysis of Stall Angle Delay in Airfoil Coupled with Spinning Cylinder</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=N.%20Kiran">N. Kiran</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20A.%20Vikas"> S. A. Vikas</a>, <a href="https://publications.waset.org/abstracts/search?q=Yatish%20Chandra"> Yatish Chandra</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Srinivasan"> S. Srinivasan </a> </p> <p class="card-text"><strong>Abstract:</strong></p> Several Centuries ago, the aerodynamic studies on rotating cylinders and spheres have started. From the observation, the rotation of a cylinder has a remarkable effect on the aerodynamic characteristics is noticed. In case of airfoils as the angle of attack increases, the drag increases with reduction in lift i.e at the critical angle of attack. If at this point a strong impulse is imparted to the boundary layer by means of a spinning cylinder, the re-energisation of boundary layer is achieved and hence delaying the boundary layer separation and stalling characteristics. Analysis of aerodynamic effects spinning cylinder either at leading edge or at trailing edge of the airfoil is carried in the past, the positioning of cylinder close to trailing edge and its effects in delaying the stall are yet to be analyzed in depth. This paper aim is to understand the combined aerodynamic effects of coupling the spinning cylinder with the airfoil closer to the Trailing edge, by considering different spin ratio of the cylinder, its location and geometrical parameters in relation to the chord of the airfoil. From the analysis, it was observed that the spinning cylinder speed of rotation and location had a impact on stalling characteristics for a prescribed free stream condition. The results predicted through CFD analysis and experimental analysis showed a raise in aerodynamic efficiency and as the spin ratio increases, increase in stalling angle of attack is noticed when compared to the airfoil without spinning cylinder. <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=airfoil" title=" airfoil"> airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=spinning%20cylinder" title=" spinning cylinder"> spinning cylinder</a>, <a href="https://publications.waset.org/abstracts/search?q=stalling" title=" stalling"> stalling</a> </p> <a href="https://publications.waset.org/abstracts/34802/analysis-of-stall-angle-delay-in-airfoil-coupled-with-spinning-cylinder" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/34802.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">440</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">98</span> Simulations of NACA 65-415 and NACA 64-206 Airfoils 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=David%20Nagy">David Nagy</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper exemplifies the influence of the purpose of an aircraft on the aerodynamic properties of its airfoil. In particular, the research takes into consideration two types of aircraft, namely cargo aircraft and military high-speed aircraft and compares their airfoil characteristics using their NACA airfoils as well as computational fluid dynamics. The results show that airfoils of aircraft designed for cargo have a heavier focus on maintaining a large lift force whereas speed-oriented airplanes focus on minimizing the drag force. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20simulation" title="aerodynamic simulation">aerodynamic simulation</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft" title=" aircraft"> aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=airfoil" title=" airfoil"> airfoil</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=lift%20to%20drag%20ratio" title=" lift to drag ratio"> lift to drag ratio</a>, <a href="https://publications.waset.org/abstracts/search?q=NACA%2064-206" title=" NACA 64-206"> NACA 64-206</a>, <a href="https://publications.waset.org/abstracts/search?q=NACA%2065-415" title=" NACA 65-415"> NACA 65-415</a> </p> <a href="https://publications.waset.org/abstracts/137836/simulations-of-naca-65-415-and-naca-64-206-airfoils-using-computational-fluid-dynamics" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/137836.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">388</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">97</span> Investigation of Flow Effects of Soundwaves Incident on an Airfoil</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Thirsa%20Sherry">Thirsa Sherry</a>, <a href="https://publications.waset.org/abstracts/search?q=Utkarsh%20Shrivastav"> Utkarsh Shrivastav</a>, <a href="https://publications.waset.org/abstracts/search?q=Kannan%20B.%20T."> Kannan B. T.</a>, <a href="https://publications.waset.org/abstracts/search?q=Iynthezhuton%20K."> Iynthezhuton K.</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The field of aerodynamics and aeroacoustics remains one of the most poignant and well-researched fields of today. The current paper aims to investigate the predominant problem concerning the effects of noise of varying frequencies and waveforms on airflow surrounding an airfoil. Using a single speaker beneath the airfoil at different positions, we wish to simulate the effects of sound directly impinging on an airfoil and study its direct effects on airflow. We wish to study the same using smoke visualization methods with incense as our smoke-generating material in a variable-speed subsonic wind tunnel. Using frequencies and wavelengths similar to those of common engine noise, we wish to simulate real-world conditions of engine noise interfering with airflow and document the arising trends. These results will allow us to look into the real-world effects of noise on airflow and how to minimize them and expand on the possible relation between waveforms and noise. The parameters used in the study include frequency, Reynolds number, waveforms, angle of attack, and the effects on airflow when varying these parameters. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=engine%20noise" title="engine noise">engine noise</a>, <a href="https://publications.waset.org/abstracts/search?q=aeroacoustics" title=" aeroacoustics"> aeroacoustics</a>, <a href="https://publications.waset.org/abstracts/search?q=acoustic%20excitation" title=" acoustic excitation"> acoustic excitation</a>, <a href="https://publications.waset.org/abstracts/search?q=low%20speed" title=" low speed"> low speed</a> </p> <a href="https://publications.waset.org/abstracts/159050/investigation-of-flow-effects-of-soundwaves-incident-on-an-airfoil" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/159050.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">92</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">96</span> Aerodynamic Performance of a Pitching Bio-Inspired Corrugated Airfoil</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Hadi%20Zarafshani">Hadi Zarafshani</a>, <a href="https://publications.waset.org/abstracts/search?q=Shidvash%20Vakilipour"> Shidvash Vakilipour</a>, <a href="https://publications.waset.org/abstracts/search?q=Shahin%20Teimori"> Shahin Teimori</a>, <a href="https://publications.waset.org/abstracts/search?q=Sara%20Barati"> Sara Barati</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In the present study, the aerodynamic performance of a rigid two-dimensional pitching bio-inspired corrugate airfoil was numerically investigated at Reynolds number of 14000. The Open Field Operations And Manipulations (OpenFOAM) computational fluid dynamic tool is used to solve flow governing equations numerically. The k-ω SST turbulence model with low Reynolds correction (k-ω SST LRC) and the pimpleDyMFOAM solver are utilized to simulate the flow field around pitching bio-airfoil. The lift and drag coefficients of the airfoil are calculated at reduced frequencies k=1.24-4.96 and the angular amplitude of A=5<sup>°</sup>-20<sup>°</sup>. Results show that in a fixed reduced frequency, the absolute value of the sectional lift and drag coefficients increase with increasing pitching amplitude. In a fixed angular amplitude, the absolute value of the lift and drag coefficients increase as the pitching reduced frequency increases. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=bio-inspired%20pitching%20airfoils" title="bio-inspired pitching airfoils">bio-inspired pitching airfoils</a>, <a href="https://publications.waset.org/abstracts/search?q=OpenFOAM" title=" OpenFOAM"> OpenFOAM</a>, <a href="https://publications.waset.org/abstracts/search?q=low%20Reynolds%20k-%CF%89%20SST%20model" title=" low Reynolds k-ω SST model"> low Reynolds k-ω SST model</a>, <a href="https://publications.waset.org/abstracts/search?q=lift%20and%20drag%20coefficients" title=" lift and drag coefficients"> lift and drag coefficients</a> </p> <a href="https://publications.waset.org/abstracts/87363/aerodynamic-performance-of-a-pitching-bio-inspired-corrugated-airfoil" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/87363.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">95</span> Thrust Enhancement on a Two Dimensional Elliptic Airfoil in a Forward Flight</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=S.%20M.%20Dash">S. M. Dash</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20B.%20Lua"> K. B. Lua</a>, <a href="https://publications.waset.org/abstracts/search?q=T.%20T.%20Lim"> T. T. Lim </a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper presents results of numerical and experimental studies on a two-dimensional (2D) flapping elliptic airfoil in a forward flight condition at Reynolds number of 5000. The study is motivated from an earlier investigation which shows that the deterioration in thrust performance of a sinusoidal heaving and pitching 2D (NACA0012) airfoil at high flapping frequency can be recovered by changing the effective angle of attack profile to square wave, sawtooth, or cosine wave shape. To better understand why such modifications lead to superior thrust performance, we take a closer look at the transient aerodynamic force behavior of an airfoil when the effective angle of attack profile changes gradually from a generic smooth trapezoidal profile to a sinusoid shape by modifying the base length of the trapezoid. The choice of using a smooth trapezoidal profile is to avoid the infinite acceleration condition encountered in the square wave profile. Our results show that the enhancement in the time-averaged thrust performance at high flapping frequency can be attributed to the delay and reduction in the drag producing valley region in the transient thrust force coefficient when the effective angle of attack profile changes from sinusoidal to trapezoidal. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=two-dimensional%20flapping%20airfoil" title="two-dimensional flapping airfoil">two-dimensional flapping airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=thrust%20performance" title=" thrust performance"> thrust performance</a>, <a href="https://publications.waset.org/abstracts/search?q=effective%20angle%20of%20attack" title=" effective angle of attack"> effective angle of attack</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=experiments" title=" experiments"> experiments</a> </p> <a href="https://publications.waset.org/abstracts/45043/thrust-enhancement-on-a-two-dimensional-elliptic-airfoil-in-a-forward-flight" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/45043.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">358</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">94</span> Numerical Investigation of the Flow Around Multi-Element Airfoils</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Taylan%20Ozturk">Taylan Ozturk</a>, <a href="https://publications.waset.org/abstracts/search?q=Osama%20Maklad"> Osama Maklad</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This study examines the aerodynamic and flow properties of a multi-element airfoil using computational fluid dynamics (CFD) research. This computational analysis aims to optimize slat design concerning lift-drag coefficients and to determine the ideal gap size between the main airfoil and the front flap. It examines the influence of varying angles of attack and the effects of varied Reynolds numbers. A NACA 2412 airfoil, equipped with custom-designed front and rear flaps, was modeled in SolidWorks and simulated in ANSYS Fluent utilizing the k-ω SST turbulence model. This study quantifies lift and drag coefficients, turbulent kinetic energy, and vorticity magnitude across various configurations. The results clearly indicate that the slat-optimized design geometry featuring a 4 mm gap provides the best performance regarding both lift and drag, with maximum efficiency achieved at a 4-degree angle of attack. Furthermore, the results indicate the initiation of stall conditions beyond 20 degrees and demonstrate how an increase in Reynolds numbers influences flow separation and turbulence patterns. In addition, the maximum L/D ratio which is 36.18 achieved. These findings enhance the comprehension of multi-element airfoil behavior, directly impacting aircraft design and operation, particularly in high-lift situations. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=multi-element%20airfoil" title="multi-element airfoil">multi-element airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD%20simulation" title=" CFD simulation"> CFD simulation</a>, <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20characteristics" title=" aerodynamic characteristics"> aerodynamic characteristics</a>, <a href="https://publications.waset.org/abstracts/search?q=Reynolds%20number%20analysis" title=" Reynolds number analysis"> Reynolds number analysis</a> </p> <a href="https://publications.waset.org/abstracts/192058/numerical-investigation-of-the-flow-around-multi-element-airfoils" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/192058.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">21</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">93</span> Transport and Mixing Phenomena Developed by Vortex Formation in Flow around Airfoil Using Lagrangian Coherent Structures</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Riaz%20Ahmad">Riaz Ahmad</a>, <a href="https://publications.waset.org/abstracts/search?q=Jiazhong%20Zhang"> Jiazhong Zhang</a>, <a href="https://publications.waset.org/abstracts/search?q=Asma%20Farooqi"> Asma Farooqi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this study, mass transport between separation bubbles and the flow around a two-dimensional airfoil are numerically investigated using Lagrangian Coherent Structures (LCSs). Finite Time Lyapunov Exponent (FTLE) technique is used for the computation to identify invariant manifolds and LCSs. Moreover, the Characteristic Base Split (CBS) scheme combined with dual time stepping technique is applied to simulate such transient flow at low Reynolds number. We then investigate the evolution of vortex structures during the transport process with the aid of LCSs. To explore the vortex formation at the surface of the airfoil, the dynamics of separatrix is also taken into account which is formed by the combination of stable-unstable manifolds. The Lagrangian analysis gives a detailed understanding of vortex dynamics and separation bubbles which plays a significant role to explore the performance of the unsteady flow generated by the airfoil. Transport process and flow separation phenomena are studied extensively to analyze the flow pattern by Lagrangian point of view. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=transport%20phenomena" title="transport phenomena">transport phenomena</a>, <a href="https://publications.waset.org/abstracts/search?q=CBS%20Method" title=" CBS Method"> CBS Method</a>, <a href="https://publications.waset.org/abstracts/search?q=vortex%20formation" title=" vortex formation"> vortex formation</a>, <a href="https://publications.waset.org/abstracts/search?q=Lagrangian%20Coherent%20Structures" title=" Lagrangian Coherent Structures"> Lagrangian Coherent Structures</a> </p> <a href="https://publications.waset.org/abstracts/108807/transport-and-mixing-phenomena-developed-by-vortex-formation-in-flow-around-airfoil-using-lagrangian-coherent-structures" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/108807.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">139</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">92</span> Design and Study of a Wind-Solar Hybrid System for Lighting Application</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Nikhil%20V.%20Nayak">Nikhil V. Nayak</a>, <a href="https://publications.waset.org/abstracts/search?q=P.%20P.%20Revankar"> P. P. Revankar</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20B.%20Gorawar"> M. B. Gorawar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Wind energy has been shown to be one of the most viable sources of renewable energy. With current technology, the low cost of wind energy is competitive with more conventional sources of energy such as coal. Most airfoil blades available for commercial grade wind turbines incorporate a straight span-wise profile and airfoil shaped cross sections. This paper is aimed at studying and designing a wind-solar hybrid system for light load application. The tools like qblade and solidworks are used to model and analyze the wind turbine system, the material used for the blade and hub is balsa wood and the tower a lattice type. The expected power output is 100 W for an average wind speed of 4.5 m/s. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=renewable%20%20energy" title="renewable energy">renewable energy</a>, <a href="https://publications.waset.org/abstracts/search?q=hybrid" title=" hybrid"> hybrid</a>, <a href="https://publications.waset.org/abstracts/search?q=airfoil%20blades" title=" airfoil blades"> airfoil blades</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20speeds" title=" wind speeds"> wind speeds</a>, <a href="https://publications.waset.org/abstracts/search?q=make-in-india" title=" make-in-india"> make-in-india</a>, <a href="https://publications.waset.org/abstracts/search?q=camber" title=" camber"> camber</a>, <a href="https://publications.waset.org/abstracts/search?q=QBlade" title=" QBlade"> QBlade</a>, <a href="https://publications.waset.org/abstracts/search?q=solidworks" title=" solidworks"> solidworks</a>, <a href="https://publications.waset.org/abstracts/search?q=balsa%20wood" title=" balsa wood"> balsa wood</a> </p> <a href="https://publications.waset.org/abstracts/42643/design-and-study-of-a-wind-solar-hybrid-system-for-lighting-application" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/42643.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">310</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">91</span> Experimental and Numerical Investigation of Flow Control Using a Novel Active Slat</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Basman%20Elhadidi">Basman Elhadidi</a>, <a href="https://publications.waset.org/abstracts/search?q=Islam%20Elqatary"> Islam Elqatary</a>, <a href="https://publications.waset.org/abstracts/search?q=Osama%20Mohamady"> Osama Mohamady</a>, <a href="https://publications.waset.org/abstracts/search?q=Hesham%20Othman"> Hesham Othman</a> </p> <p class="card-text"><strong>Abstract:</strong></p> An active slat is developed to increase the lift and delay the separation for a DU96-W180 airfoil. The active slat is a fixed slat that can be closed, fully opened or intermittently opened by a rotating vane depending on the need. Experimental results show that the active slat has reduced the mean pressure and increased the mean velocity on the suction side of the airfoil for all positive angles of attack, indicating an increase of lift. The experimental data and numerical simulations also show that the direction of actuator vane rotation can influence the mixing of the flow streams on the suction side and hence influence the aerodynamic performance. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=active%20slat" title="active slat">active slat</a>, <a href="https://publications.waset.org/abstracts/search?q=flow%20control" title=" flow control"> flow control</a>, <a href="https://publications.waset.org/abstracts/search?q=DU96-W180%20airfoil" title=" DU96-W180 airfoil"> DU96-W180 airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=flow%20streams" title=" flow streams"> flow streams</a> </p> <a href="https://publications.waset.org/abstracts/20582/experimental-and-numerical-investigation-of-flow-control-using-a-novel-active-slat" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/20582.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">378</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">90</span> Numerical Investigation of Improved Aerodynamic Performance of a NACA 0015 Airfoil Using Synthetic Jet</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=K.%20Boualem">K. Boualem</a>, <a href="https://publications.waset.org/abstracts/search?q=T.%20Yahiaoui"> T. Yahiaoui</a>, <a href="https://publications.waset.org/abstracts/search?q=A.%20Azzi"> A. Azzi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Numerical investigations are performed to analyze the flow behavior over NACA0015 and to evaluate the efficiency of synthetic jet as active control device. The second objective of this work is to investigate the influence of momentum coefficient of synthetic jet on the flow behaviour. The unsteady Reynolds-averaged Navier-Stokes equations of the turbulent flow are solved using, k-ω SST provided by ANSYS CFX-CFD code. The model presented in this paper is a comprehensive representation of the information found in the literature. Comparison of obtained numerical flow parameters with the experimental ones shows that the adopted computational procedure reflects nearly the real flow nature. Also, numerical results state that use of synthetic jets devices has positive effects on the flow separation, and thus, aerodynamic performance improvement of NACA0015 airfoil. It can also be observed that the use of synthetic jet increases the lift coefficient about 13.3% and reduces the drag coefficient about 52.7%. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=active%20control" title="active control">active control</a>, <a href="https://publications.waset.org/abstracts/search?q=synthetic%20jet" title=" synthetic jet"> synthetic jet</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=CFD" title=" CFD"> CFD</a> </p> <a href="https://publications.waset.org/abstracts/58346/numerical-investigation-of-improved-aerodynamic-performance-of-a-naca-0015-airfoil-using-synthetic-jet" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/58346.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">313</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">89</span> Numerical Analysis of a Mechanism for the Morphology in the Extrados of an Airfoil</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=E.%20R.%20Jimenez%20Barron">E. R. Jimenez Barron</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20Castillo%20Morales"> M. Castillo Morales</a>, <a href="https://publications.waset.org/abstracts/search?q=D.%20F.%20Ram%C3%ADrez%20Morales"> D. F. Ramírez Morales</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The study of the morphology (shape change) in wings leads to the optimization of aerodynamic characteristics in an aircraft, so for the development and implementation of a change in the structure and shape of an airfoil, in this case the extrados, helps to increase the aerodynamic performance of an aircraft at different operating velocities, according to the required mission profile. A previous work on morphology is continued where the 'initial' profile is the NACA 4415 and as a new profile 'objective' the FUSION. The objective of this work is the dimensioning of the elements of the mechanism used to achieve the required changes. We consulted the different materials used in the aeronautics industry, as well as new materials in this area that could contribute to the good performance of the mechanism without negatively affecting the aerodynamics. These results allow evaluating the performance of a wing with variable extrados with respect to the defined morphology. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=numerical%20analysis" title="numerical analysis">numerical analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=mechanisms" title=" mechanisms"> mechanisms</a>, <a href="https://publications.waset.org/abstracts/search?q=morphing%20airfoil" title=" morphing airfoil"> morphing airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=morphing%20wings" title=" morphing wings"> morphing wings</a> </p> <a href="https://publications.waset.org/abstracts/77600/numerical-analysis-of-a-mechanism-for-the-morphology-in-the-extrados-of-an-airfoil" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/77600.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">236</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">88</span> Structural and Modal Analyses of an s1223 High-Lift Airfoil Wing for Drone Design</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Johnson%20Okoduwa%20Imumbhon">Johnson Okoduwa Imumbhon</a>, <a href="https://publications.waset.org/abstracts/search?q=Mohammad%20Didarul%20Alam"> Mohammad Didarul Alam</a>, <a href="https://publications.waset.org/abstracts/search?q=Yiding%20Cao"> Yiding Cao</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Structural analyses are commonly employed to test the integrity of aircraft component systems in the design stage to demonstrate the capability of the structural components to withstand what it was designed for, as well as to predict potential failure of the components. The analyses are also essential for weight minimization and selecting the most resilient materials that will provide optimal outcomes. This research focuses on testing the structural nature of a high-lift low Reynolds number airfoil profile design, the Selig S1223, under certain loading conditions for a drone model application. The wing (ribs, spars, and skin) of the drone model was made of carbon fiber-reinforced polymer and designed in SolidWorks, while the finite element analysis was carried out in ANSYS mechanical in conjunction with the lift and drag forces that were derived from the aerodynamic airfoil analysis. Additionally, modal analysis was performed to calculate the natural frequencies and the mode shapes of the wing structure. The structural strain and stress determined the minimal deformations under the wing loading conditions, and the modal analysis showed the prominent modes that were excited by the given forces. The research findings from the structural analysis of the S1223 high-lift airfoil indicated that it is applicable for use in an unmanned aerial vehicle as well as a novel reciprocating-airfoil-driven vertical take-off and landing (VTOL) drone model. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=CFRP" title="CFRP">CFRP</a>, <a href="https://publications.waset.org/abstracts/search?q=finite%20element%20analysis" title=" finite element analysis"> finite element analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=high-lift" title=" high-lift"> high-lift</a>, <a href="https://publications.waset.org/abstracts/search?q=S1223" title=" S1223"> S1223</a>, <a href="https://publications.waset.org/abstracts/search?q=strain" title=" strain"> strain</a>, <a href="https://publications.waset.org/abstracts/search?q=stress" title=" stress"> stress</a>, <a href="https://publications.waset.org/abstracts/search?q=VTOL" title=" VTOL"> VTOL</a> </p> <a href="https://publications.waset.org/abstracts/134309/structural-and-modal-analyses-of-an-s1223-high-lift-airfoil-wing-for-drone-design" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/134309.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">228</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">87</span> Laminar Separation Bubble Prediction over an Airfoil Using Transition SST Turbulence Model on Moderate Reynolds Number</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Younes%20El%20Khchine">Younes El Khchine</a>, <a href="https://publications.waset.org/abstracts/search?q=Mohammed%20Sriti"> Mohammed Sriti</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A parametric study has been conducted to analyse the flow around S809 airfoil of a wind turbine in order to better understand the characteristics and effects of laminar separation bubble (LSB) on aerodynamic design for maximizing wind turbine efficiency. Numerical simulations were performed at low Reynolds numbers by solving the Unsteady Reynolds Averaged Navier-Stokes (URANS) equations based on C-type structural mesh and using the γ-Reθt turbulence model. A two-dimensional study was conducted for the chord Reynolds number of 1×10⁵ and angles of attack (AoA) between 0 and 20.15 degrees. The simulation results obtained for the aerodynamic coefficients at various angles of attack (AoA) were compared with XFoil results. A sensitivity study was performed to examine the effects of Reynolds number and free-stream turbulence intensity on the location and length of the laminar separation bubble and the aerodynamic performances of wind turbines. The results show that increasing the Reynolds number leads to a delay in the laminar separation on the upper surface of the airfoil. The increase in Reynolds number leads to an accelerated transition process, and the turbulent reattachment point moves closer to the leading edge owing to an earlier reattachment of the turbulent shear layer. This leads to a considerable reduction in the length of the separation bubble as the Reynolds number is increased. The increase in the level of free-stream turbulence intensity leads to a decrease in separation bubble length and an increase in the lift coefficient while having negligible effects on the stall angle. When the AoA increased, the bubble on the suction airfoil surface was found to move upstream to the leading edge of the airfoil, that causes earlier laminar separation. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=laminar%20separation%20bubble" title="laminar separation bubble">laminar separation bubble</a>, <a href="https://publications.waset.org/abstracts/search?q=turbulence%20intensity" title=" turbulence intensity"> turbulence intensity</a>, <a href="https://publications.waset.org/abstracts/search?q=S809%20airfoil" title=" S809 airfoil"> S809 airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=transition%20model" title=" transition model"> transition model</a>, <a href="https://publications.waset.org/abstracts/search?q=Reynolds%20number" title=" Reynolds number"> Reynolds number</a> </p> <a href="https://publications.waset.org/abstracts/179140/laminar-separation-bubble-prediction-over-an-airfoil-using-transition-sst-turbulence-model-on-moderate-reynolds-number" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/179140.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">83</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">86</span> Study on the Geometric Similarity in Computational Fluid Dynamics Calculation and the Requirement of Surface Mesh Quality</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Qian%20Yi%20Ooi">Qian Yi Ooi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> At present, airfoil parameters are still designed and optimized according to the scale of conventional aircraft, and there are still some slight deviations in terms of scale differences. However, insufficient parameters or poor surface mesh quality is likely to occur if these small deviations are embedded in a future civil aircraft with a size that is quite different from conventional aircraft, such as a blended-wing-body (BWB) aircraft with future potential, resulting in large deviations in geometric similarity in computational fluid dynamics (CFD) simulations. To avoid this situation, the study on the CFD calculation on the geometric similarity of airfoil parameters and the quality of the surface mesh is conducted to obtain the ability of different parameterization methods applied on different airfoil scales. The research objects are three airfoil scales, including the wing root and wingtip of conventional civil aircraft and the wing root of the giant hybrid wing, used by three parameterization methods to compare the calculation differences between different sizes of airfoils. In this study, the constants including NACA 0012, a Reynolds number of 10 million, an angle of attack of zero, a C-grid for meshing, and the k-epsilon (k-ε) turbulence model are used. The experimental variables include three airfoil parameterization methods: point cloud method, B-spline curve method, and class function/shape function transformation (CST) method. The airfoil dimensions are set to 3.98 meters, 17.67 meters, and 48 meters, respectively. In addition, this study also uses different numbers of edge meshing and the same bias factor in the CFD simulation. Studies have shown that with the change of airfoil scales, different parameterization methods, the number of control points, and the meshing number of divisions should be used to improve the accuracy of the aerodynamic performance of the wing. When the airfoil ratio increases, the most basic point cloud parameterization method will require more and larger data to support the accuracy of the airfoil’s aerodynamic performance, which will face the severe test of insufficient computer capacity. On the other hand, when using the B-spline curve method, average number of control points and meshing number of divisions should be set appropriately to obtain higher accuracy; however, the quantitative balance cannot be directly defined, but the decisions should be made repeatedly by adding and subtracting. Lastly, when using the CST method, it is found that limited control points are enough to accurately parameterize the larger-sized wing; a higher degree of accuracy and stability can be obtained by using a lower-performance computer. <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=computational%20fluid%20dynamics" title=" computational fluid dynamics"> computational fluid dynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=geometric%20similarity" title=" geometric similarity"> geometric similarity</a>, <a href="https://publications.waset.org/abstracts/search?q=surface%20mesh%20quality" title=" surface mesh quality"> surface mesh quality</a> </p> <a href="https://publications.waset.org/abstracts/138879/study-on-the-geometric-similarity-in-computational-fluid-dynamics-calculation-and-the-requirement-of-surface-mesh-quality" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/138879.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">222</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=dihedral%20airfoil&page=2">2</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=dihedral%20airfoil&page=3">3</a></li> <li class="page-item"><a class="page-link" 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