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Search results for: aerodynamic performance

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</div> </nav> </div> </header> <main> <div class="container mt-4"> <div class="row"> <div class="col-md-9 mx-auto"> <form method="get" action="https://publications.waset.org/abstracts/search"> <div id="custom-search-input"> <div class="input-group"> <i class="fas fa-search"></i> <input type="text" class="search-query" name="q" placeholder="Author, Title, Abstract, Keywords" value="aerodynamic performance"> <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> 13052</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: aerodynamic performance</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">13052</span> Aerodynamic Analysis of Vehicles</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=E.%20T.%20L.%20C%C3%B6uras%20Ford">E. T. L. Cöuras Ford</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20A.%20C.%20Vale"> V. A. C. Vale</a>, <a href="https://publications.waset.org/abstracts/search?q=J.%20U.%20L.%20Mendes"> J. U. L. Mendes</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Two of the objective principal in the study of the aerodynamics of vehicles are the safety and the acting. Those objectives can be reached through the development of devices modify the drainage of air about of the vehicle and also through alterations in the way of the external surfaces. The front lowest profile of the vehicle, for instance, has great influence on the coefficient of aerodynamic penetration (Cx) and later on great part of the pressure distribution along the surface of the vehicle. The objective of this work was of analyzing the aerodynamic behavior that it happens on some types the trucks of vehicles, based on experimentation in aerodynamic tunnel, seeking to determine the aerodynamic efficiency of each one of them. <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=vehicles" title=" vehicles"> vehicles</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20tunnel" title=" wind tunnel"> wind tunnel</a>, <a href="https://publications.waset.org/abstracts/search?q=safety" title=" safety"> safety</a>, <a href="https://publications.waset.org/abstracts/search?q=acting" title=" acting"> acting</a> </p> <a href="https://publications.waset.org/abstracts/18365/aerodynamic-analysis-of-vehicles" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/18365.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">499</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">13051</span> Aerodynamic Heating and Drag Reduction of Pegasus-XL Satellite Launch Vehicle</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Syed%20Muhammad%20Awais%20Tahir">Syed Muhammad Awais Tahir</a>, <a href="https://publications.waset.org/abstracts/search?q=Syed%20Hossein%20Raza%20Hamdani"> Syed Hossein Raza Hamdani</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In the last two years, there has been a substantial increase in the rate of satellite launches. To keep up with the technology, it is imperative that the launch cost must be made affordable, especially in developing and underdeveloped countries. Launch cost is directly affected by the launch vehicle’s aerodynamic performance. Pegasus-XL SLV (Satellite Launch Vehicle) has been serving as a commercial SLV for the last 26 years, commencing its commercial flight operation from the six operational sites all around the US and Europe, and the Marshal Islands. Aerodynamic heating and drag contribute largely to Pegasus’s flight performance. The objective of this study is to reduce the aerodynamic heating and drag on Pegasus’s body significantly for supersonic and hypersonic flight regimes. Aerodynamic data for Pegasus’s first flight has been validated through CFD (Computational Fluid Dynamics), and then drag and aerodynamic heating is reduced by using a combination of a forward-facing cylindrical spike and a conical aero-disk at the actual operational flight conditions. CFD analysis using ANSYS fluent will be carried out for Mach no. ranges from 0.83 to 7.8, and AoA (Angle of Attack) ranges from -4 to +24 degrees for both simple and spiked-configuration, and then the comparison will be drawn using a variety of graphs and contours. Expected drag reduction for supersonic flight is to be around 15% to 25%, and for hypersonic flight is to be around 30% to 50%, especially for AoA < 15⁰. A 5% to 10% reduction in aerodynamic heating is expected to be achieved for hypersonic regions. In conclusion, the aerodynamic performance of air-launched Pegasus-XL SLV can be further enhanced, leading to its optimal fuel usage to achieve a more economical orbital flight. <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=pegasus-XL" title=" pegasus-XL"> pegasus-XL</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=aerodynamic%20heating" title=" aerodynamic heating"> aerodynamic heating</a>, <a href="https://publications.waset.org/abstracts/search?q=satellite%20launch%20vehicle" title=" satellite launch vehicle"> satellite launch vehicle</a>, <a href="https://publications.waset.org/abstracts/search?q=SLV" title=" SLV"> SLV</a>, <a href="https://publications.waset.org/abstracts/search?q=spike" title=" spike"> spike</a>, <a href="https://publications.waset.org/abstracts/search?q=aero-disk" title=" aero-disk"> aero-disk</a> </p> <a href="https://publications.waset.org/abstracts/150232/aerodynamic-heating-and-drag-reduction-of-pegasus-xl-satellite-launch-vehicle" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/150232.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">107</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">13050</span> Investigation of the Aerodynamic Characteristics of a Vertical Take-Off and Landing Mini Unmanned Aerial Vehicle Configuration</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Amir%20Abdelqodus">Amir Abdelqodus</a>, <a href="https://publications.waset.org/abstracts/search?q=Mario%20Shehata"> Mario Shehata</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The purpose of the paper is to model and evaluate the aerodynamic coefficients and stability derivatives of a Vertical, Take-off and Landing Unmanned Aerial Vehicle configuration (VTOL UAV), which is a fixed wing UAV and a quad-copter hybrid capable of both vertical and conventional take-off and/or landing. The aerodynamic analysis of this configuration was carried out using CFD commercial package Ansys Fluent. Also, the aerodynamic coefficients for the case of the UAV without the quad-copter is carried out analytically using MATLAB programmed codes, and the resulting data is verified using Lifting Line Theory and potential method programs. The two results are then compared to understand the effect of adding the quad-copter on the aerodynamic performance of the UAV. <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=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=potential%20flow" title=" potential flow"> potential flow</a>, <a href="https://publications.waset.org/abstracts/search?q=UAV" title=" UAV"> UAV</a>, <a href="https://publications.waset.org/abstracts/search?q=VTOL" title=" VTOL"> VTOL</a> </p> <a href="https://publications.waset.org/abstracts/81527/investigation-of-the-aerodynamic-characteristics-of-a-vertical-take-off-and-landing-mini-unmanned-aerial-vehicle-configuration" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/81527.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">445</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">13049</span> Using Divergent Nozzle with Aerodynamic Lens to Focus Nanoparticles</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Hasan%20Jumaah%20Mrayeh">Hasan Jumaah Mrayeh</a>, <a href="https://publications.waset.org/abstracts/search?q=Fue-Sang%20Lien"> Fue-Sang Lien</a> </p> <p class="card-text"><strong>Abstract:</strong></p> ANSYS Fluent will be used to simulate Computational Fluid Dynamics (CFD) for an efficient lens and nozzle design which will be explained in this paper. We have designed and characterized an aerodynamic lens and a divergent nozzle for focusing flow that transmits sub 25 nm particles through the aerodynamic lens. The design of the lens and nozzle has been improved using CFD for particle trajectories. We obtained a case for calculating nanoparticles (25 nm) flowing through the aerodynamic lens and divergent nozzle. Nanoparticles are transported by air, which is pumped into the aerodynamic lens through the nozzle at 1 atmospheric pressure. We have also developed a computational methodology that can determine the exact focus characteristics of aerodynamic lens systems. Particle trajectories were traced using the Lagrange approach. The simulation shows the ability of the aerodynamic lens to focus on 25 nm particles after using a divergent nozzle. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20lens" title="aerodynamic lens">aerodynamic lens</a>, <a href="https://publications.waset.org/abstracts/search?q=divergent%20nozzle" title=" divergent nozzle"> divergent nozzle</a>, <a href="https://publications.waset.org/abstracts/search?q=ANSYS%20Fluent" title=" ANSYS Fluent"> ANSYS Fluent</a>, <a href="https://publications.waset.org/abstracts/search?q=Lagrange%20approach" title=" Lagrange approach"> Lagrange approach</a> </p> <a href="https://publications.waset.org/abstracts/106210/using-divergent-nozzle-with-aerodynamic-lens-to-focus-nanoparticles" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/106210.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">306</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">13048</span> Experimental and CFD of Desgined Small Wind Turbine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Tarek%20A.%20Mekail">Tarek A. Mekail</a>, <a href="https://publications.waset.org/abstracts/search?q=Walid%20M.%20A.%20Elmagid"> Walid M. A. Elmagid</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Many researches have concentrated on improving the aerodynamic performance of wind turbine blade through testing and theoretical studies. A small wind turbine blade is designed, fabricated and tested. The power performance of small horizontal axis wind turbines is simulated in details using Computational Fluid Dynamic (CFD). The three-dimensional CFD models are presented using ANSYS-CFX v13 software for predicting the performance of a small horizontal axis wind turbine. The simulation results are compared with the experimental data measured from a small wind turbine model, which designed according to a vehicle-based test system. The analysis of wake effect and aerodynamic of the blade can be carried out when the rotational effect was simulated. Finally, comparison between experimental, numerical and analytical performance has been done. The comparison is fairly good. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=small%20wind%20turbine" title="small wind turbine">small wind turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD%20of%20wind%20turbine" title=" CFD of wind turbine"> CFD of wind turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=performance%20of%20wind%20turbine" title=" performance of wind turbine"> performance of wind turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=test%20of%20small%20wind%20turbine" title=" test of small wind turbine"> test of small wind turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20turbine%20aerodynamic" title=" wind turbine aerodynamic"> wind turbine aerodynamic</a>, <a href="https://publications.waset.org/abstracts/search?q=3D%20model" title=" 3D model"> 3D model</a> </p> <a href="https://publications.waset.org/abstracts/18446/experimental-and-cfd-of-desgined-small-wind-turbine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/18446.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">542</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">13047</span> Optimization of the Aerodynamic Performances of an Unmanned Aerial Vehicle</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Fares%20Senouci">Fares Senouci</a>, <a href="https://publications.waset.org/abstracts/search?q=Bachir%20Imine"> Bachir Imine</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This document provides numerical and experimental optimization of the aerodynamic performance of a drone equipped with three types of horizontal stabilizer. To build this optimal configuration, an experimental and numerical study was conducted on three parameters: the geometry of the stabilizer (horizontal form or reverse V form), the position of the horizontal stabilizer (up or down), and the landing gear position (closed or open). The results show that up-stabilizer position with respect to the horizontal plane of the fuselage provides better aerodynamic performance, and that the landing gear increases the lift in the zone of stability, that is to say where the flow is not separated. <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=drag" title=" drag"> drag</a>, <a href="https://publications.waset.org/abstracts/search?q=lift" title=" lift"> lift</a>, <a href="https://publications.waset.org/abstracts/search?q=turbulence%20model" title=" turbulence model"> turbulence model</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20tunnel" title=" wind tunnel"> wind tunnel</a> </p> <a href="https://publications.waset.org/abstracts/68885/optimization-of-the-aerodynamic-performances-of-an-unmanned-aerial-vehicle" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/68885.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">252</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">13046</span> Application of the Total Least Squares Estimation Method for an Aircraft Aerodynamic Model Identification</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Zaouche%20Mohamed">Zaouche Mohamed</a>, <a href="https://publications.waset.org/abstracts/search?q=Amini%20Mohamed"> Amini Mohamed</a>, <a href="https://publications.waset.org/abstracts/search?q=Foughali%20Khaled"> Foughali Khaled</a>, <a href="https://publications.waset.org/abstracts/search?q=Aitkaid%20Souhila"> Aitkaid Souhila</a>, <a href="https://publications.waset.org/abstracts/search?q=Bouchiha%20Nihad%20Sarah"> Bouchiha Nihad Sarah</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The aerodynamic coefficients are important in the evaluation of an aircraft performance and stability-control characteristics. These coefficients also can be used in the automatic flight control systems and mathematical model of flight simulator. The study of the aerodynamic aspect of flying systems is a reserved domain and inaccessible for the developers. Doing tests in a wind tunnel to extract aerodynamic forces and moments requires a specific and expensive means. Besides, the glaring lack of published documentation in this field of study makes the aerodynamic coefficients determination complicated. This work is devoted to the identification of an aerodynamic model, by using an aircraft in virtual simulated environment. We deal with the identification of the system, we present an environment framework based on Software In the Loop (SIL) methodology and we use Microsoft<sup>TM</sup> Flight Simulator (FS-2004) as the environment for plane simulation. We propose The Total Least Squares Estimation technique (TLSE) to identify the aerodynamic parameters, which are unknown, variable, classified and used in the expression of the piloting law. In this paper, we define each aerodynamic coefficient as the mean of its numerical values. All other variations are considered as modeling uncertainties that will be compensated by the robustness of the piloting control. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft%20aerodynamic%20model" title="aircraft aerodynamic model">aircraft aerodynamic model</a>, <a href="https://publications.waset.org/abstracts/search?q=total%20least%20squares%20estimation" title=" total least squares estimation"> total least squares estimation</a>, <a href="https://publications.waset.org/abstracts/search?q=piloting%20the%20aircraft" title=" piloting the aircraft"> piloting the aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=robust%20control" title=" robust control"> robust control</a>, <a href="https://publications.waset.org/abstracts/search?q=Microsoft%20Flight%20Simulator" title=" Microsoft Flight Simulator"> Microsoft Flight Simulator</a>, <a href="https://publications.waset.org/abstracts/search?q=MQ-1%20predator" title=" MQ-1 predator"> MQ-1 predator</a> </p> <a href="https://publications.waset.org/abstracts/44416/application-of-the-total-least-squares-estimation-method-for-an-aircraft-aerodynamic-model-identification" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/44416.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">287</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">13045</span> Research on Aerodynamic Brake Device for High-Speed Train</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=S.%20Yun">S. Yun</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20Kwak"> M. Kwak </a> </p> <p class="card-text"><strong>Abstract:</strong></p> This study is about an aerodynamic brake device for a high-speed train. In order to apply an aerodynamic brake device, an influence of the aerodynamic brake device on a high-speed train was studied aerodynamically, acoustically and dynamically. Wind tunnel test was conducted to predict an effect of braking distance reduction with a scale model of 1/30. Aerodynamic drag increases by 244% with a brake panel of a 90 degree angle. Braking distance for an emergency state was predicted to decrease by 13%. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20brake" title="aerodynamic brake">aerodynamic brake</a>, <a href="https://publications.waset.org/abstracts/search?q=braking%20distance" title=" braking distance"> braking distance</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=high-speed%20train" title=" high-speed train"> high-speed train</a>, <a href="https://publications.waset.org/abstracts/search?q=wind-tunnel%20test" title=" wind-tunnel test"> wind-tunnel test</a> </p> <a href="https://publications.waset.org/abstracts/65559/research-on-aerodynamic-brake-device-for-high-speed-train" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/65559.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">13044</span> Aerodynamic Analysis of a Frontal Deflector for Vehicles</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=C.%20Mal%C3%A7a">C. Malça</a>, <a href="https://publications.waset.org/abstracts/search?q=N.%20Alves"> N. Alves</a>, <a href="https://publications.waset.org/abstracts/search?q=A.%20Mateus"> A. Mateus</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This work was one of the tasks of the Manufacturing2Client project, whose objective was to develop a frontal deflector to be commercialized in the automotive industry, using new project and manufacturing methods. In this task, in particular, it was proposed to develop the ability to predict computationally the aerodynamic influence of flow in vehicles, in an effort to reduce fuel consumption in vehicles from class 3 to 8. With this aim, two deflector models were developed and their aerodynamic performance analyzed. The aerodynamic study was done using the Computational Fluid Dynamics (CFD) software Ansys CFX and allowed the calculation of the drag coefficient caused by the vehicle motion for the different configurations considered. Moreover, the reduction of diesel consumption and carbon dioxide (CO2) emissions associated with the optimized deflector geometry could be assessed. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=erodynamic%20analysis" title="erodynamic analysis">erodynamic analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=CO2%20emissions" title=" CO2 emissions"> CO2 emissions</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=frontal%20deflector" title=" frontal deflector"> frontal deflector</a>, <a href="https://publications.waset.org/abstracts/search?q=fuel%20consumption" title=" fuel consumption"> fuel consumption</a> </p> <a href="https://publications.waset.org/abstracts/17891/aerodynamic-analysis-of-a-frontal-deflector-for-vehicles" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/17891.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">407</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">13043</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">13042</span> Computational Fluid Dynamics-Coupled Optimisation Strategy for Aerodynamic Design</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Anvar%20Atayev">Anvar Atayev</a>, <a href="https://publications.waset.org/abstracts/search?q=Karl%20Steinborn"> Karl Steinborn</a>, <a href="https://publications.waset.org/abstracts/search?q=Aleksander%20Lovric"> Aleksander Lovric</a>, <a href="https://publications.waset.org/abstracts/search?q=Saif%20Al-Ibadi"> Saif Al-Ibadi</a>, <a href="https://publications.waset.org/abstracts/search?q=Jorg%20Fliege"> Jorg Fliege</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this paper, we present results obtained from optimising the aerodynamic performance of aerostructures in external ow. The optimisation method used was developed to efficiently handle multi-variable problems with numerous black-box objective functions and constraints. To demonstrate these capabilities, a series of CFD problems were considered; (1) a two-dimensional NACA aerofoil with three variables, (2) a two-dimensional morphing aerofoil with 17 variables, and (3) a three-dimensional morphing aeroplane tail with 33 variables. The objective functions considered were related to combinations of the mean aerodynamic coefficients, as well as their relative variations/oscillations. It was observed that for each CFD problem, an improved objective value was found. Notably, the scale-up in variables for the latter problems did not greatly hinder optimisation performance. This makes the method promising for scaled-up CFD problems, which require considerable computational resources. <p class="card-text"><strong>Keywords:</strong> <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=optimisation%20algorithms" title=" optimisation algorithms"> optimisation algorithms</a>, <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20design" title=" aerodynamic design"> aerodynamic design</a>, <a href="https://publications.waset.org/abstracts/search?q=engineering%20design" title=" engineering design"> engineering design</a> </p> <a href="https://publications.waset.org/abstracts/152822/computational-fluid-dynamics-coupled-optimisation-strategy-for-aerodynamic-design" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/152822.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">120</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">13041</span> Aerodynamic Prediction and Performance Analysis for Mars Science Laboratory Entry Vehicle</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Tang%20Wei">Tang Wei</a>, <a href="https://publications.waset.org/abstracts/search?q=Yang%20Xiaofeng"> Yang Xiaofeng</a>, <a href="https://publications.waset.org/abstracts/search?q=Gui%20Yewei"> Gui Yewei</a>, <a href="https://publications.waset.org/abstracts/search?q=Du%20Yanxia"> Du Yanxia</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Complex lifting entry was selected for precise landing performance during the Mars Science Laboratory entry. This study aims to develop the three-dimensional numerical method for precise computation and the surface panel method for rapid engineering prediction. Detailed flow field analysis for Mars exploration mission was performed by carrying on a series of fully three-dimensional Navier-Stokes computations. The static aerodynamic performance was then discussed, including the surface pressure, lift and drag coefficient, lift-to-drag ratio with the numerical and engineering method. Computation results shown that the shock layer is thin because of lower effective specific heat ratio, and that calculated results from both methods agree well with each other, and is consistent with the reference data. Aerodynamic performance analysis shows that CG location determines trim characteristics and pitch stability, and certain radially and axially shift of the CG location can alter the capsule lifting entry performance, which is of vital significance for the aerodynamic configuration des0ign and inner instrument layout of the Mars entry capsule. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=Mars%20entry%20capsule" title="Mars entry capsule">Mars entry capsule</a>, <a href="https://publications.waset.org/abstracts/search?q=static%20aerodynamics" title=" static aerodynamics"> static aerodynamics</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=hypersonic" title=" hypersonic"> hypersonic</a> </p> <a href="https://publications.waset.org/abstracts/22909/aerodynamic-prediction-and-performance-analysis-for-mars-science-laboratory-entry-vehicle" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/22909.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">299</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">13040</span> Numerical and Experimental Investigation of the Aerodynamic Performances of Counter-Rotating Rotors</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ibrahim%20Beldjilali">Ibrahim Beldjilali</a>, <a href="https://publications.waset.org/abstracts/search?q=Adel%20Ghenaiet"> Adel Ghenaiet</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The contra-rotating axial machine is a promising solution for several applications, where high pressure and efficiencies are needed. Also, they allow reducing the speed of rotation, the radial spacing and a better flexibility of use. However, this requires a better understanding of their operation, including the influence of second rotor on the overall aerodynamic performances. This work consisted of both experimental and numerical studies to characterize this counter-rotating fan, especially the analysis of the effects of the blades stagger angle and the inter-distance between the rotors. The experimental study served to validate the computational fluid dynamics model (CFD) used in the simulations. The numerical study permitted to cover a wider range of parameter and deeper investigation on flow structures details, including the effects of blade stagger angle and inter-distance, associated with the interaction between the rotors. As a result, there is a clear improvement in aerodynamic performance compared with a conventional machine. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20performance" title="aerodynamic performance">aerodynamic performance</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=counter%20rotating%20rotors" title=" counter rotating rotors"> counter rotating rotors</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=experimental%20study" title=" experimental study"> experimental study</a> </p> <a href="https://publications.waset.org/abstracts/107619/numerical-and-experimental-investigation-of-the-aerodynamic-performances-of-counter-rotating-rotors" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/107619.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">159</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">13039</span> A Parametric Study on Aerodynamic Performance of Tyre Using CFD</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Sowntharya%20L.">Sowntharya L.</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Aerodynamics is the most important factor when it comes to resistive forces such as lift, drag and side forces acting on the vehicle. In passenger vehicles, reducing the drag will not only unlock the door for higher achievable speed but will also reduce the fuel consumption of the vehicle. Generally, tyre contributes significantly to the overall aerodynamics of the vehicle. Hence, understanding the air-flow behaviour around the tyre is vital to optimize the aerodynamic performance in the early stage of design process. Nowadays, aerodynamic simulation employing Computational Fluid Dynamics (CFD) is gaining more importance as it reduces the number of physical wind-tunnel experiments during vehicle development process. This research develops a methodology to predict aerodynamic drag of a standalone tyre using Numerical CFD Solver and to validate the same using a wind tunnel experiment. A parametric study was carried out on different tread pattern tyres such as slick, circumferential groove & patterned tyre in stationary and rotating boundary conditions. In order to represent wheel rotation contact with the ground, moving reference frame (MRF) approach was used in this study. Aerodynamic parameters such as drag lift & air flow behaviour around the tire were simulated and compared with experimental results. <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=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=MRF" title=" MRF"> MRF</a>, <a href="https://publications.waset.org/abstracts/search?q=wind-tunnel" title=" wind-tunnel"> wind-tunnel</a> </p> <a href="https://publications.waset.org/abstracts/134331/a-parametric-study-on-aerodynamic-performance-of-tyre-using-cfd" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/134331.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">194</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">13038</span> Quantification of Aerodynamic Variables Using Analytical Technique and Computational Fluid Dynamics</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Adil%20Loya">Adil Loya</a>, <a href="https://publications.waset.org/abstracts/search?q=Kamran%20Maqsood"> Kamran Maqsood</a>, <a href="https://publications.waset.org/abstracts/search?q=Muhammad%20Duraid"> Muhammad Duraid</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Aerodynamic stability coefficients are necessary to be known before any unmanned aircraft flight is performed. This requires expertise on aerodynamics and stability control of the aircraft. To enable efficacious performance of aircraft requires that a well-defined flight path and aerodynamics should be defined beforehand. This paper presents a study on the aerodynamics of an unmanned aero vehicle (UAV) during flight conditions. Current research holds comparative studies of different parameters for flight aerodynamic, measured using two different open source analytical software programs. These software packages are DATCOM and XLRF5, which help in depicting the flight aerodynamic variables. Computational fluid dynamics (CFD) was also used to perform aerodynamic analysis for which Star CCM+ was used. Output trends of the study demonstrate high accuracies between the two software programs with that of CFD. It can be seen that the Coefficient of Lift (CL) obtained from DATCOM and XFLR is similar to CL of CFD simulation. In the similar manner, other potential aerodynamic stability parameters obtained from analytical software are in good agreement with CFD. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=XFLR5" title="XFLR5">XFLR5</a>, <a href="https://publications.waset.org/abstracts/search?q=DATCOM" title=" DATCOM"> DATCOM</a>, <a href="https://publications.waset.org/abstracts/search?q=computational%20fluid%20dynamic" title=" computational fluid dynamic"> computational fluid dynamic</a>, <a href="https://publications.waset.org/abstracts/search?q=unmanned%20aero%20vehicle" title=" unmanned aero vehicle"> unmanned aero vehicle</a> </p> <a href="https://publications.waset.org/abstracts/89932/quantification-of-aerodynamic-variables-using-analytical-technique-and-computational-fluid-dynamics" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/89932.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">298</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">13037</span> Formula Student Car: Design, Analysis and Lap Time Simulation</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Rachit%20Ahuja">Rachit Ahuja</a>, <a href="https://publications.waset.org/abstracts/search?q=Ayush%20Chugh"> Ayush Chugh</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Aerodynamic forces and moments, as well as tire-road forces largely affects the maneuverability of the vehicle. Car manufacturers are largely fascinated and influenced by various aerodynamic improvements made in formula cars. There is constant effort of applying these aerodynamic improvements in road vehicles. In motor racing, the key differentiating factor in a high performance car is its ability to maintain highest possible acceleration in appropriate direction. One of the main areas of concern in motor racing is balance of aerodynamic forces and stream line the flow of air across the body of the vehicle. At present, formula racing cars are regulated by stringent FIA norms, there are constrains for dimensions of the vehicle, engine capacity etc. So one of the fields in which there is a large scope of improvement is aerodynamics of the vehicle. In this project work, an attempt has been made to design a formula- student (FS) car, improve its aerodynamic characteristics through steady state CFD simulations and simultaneously calculate its lap time. Initially, a CAD model of a formula student car is made using SOLIDWORKS as per the given dimensions and a steady-state external air-flow simulation is performed on the baseline model of the formula student car without any add on device to evaluate and analyze the air-flow pattern around the car and aerodynamic forces using FLUENT Solver. A detailed survey on different add-on devices used in racing application like: - front wing, diffuser, shark pin, T- wing etc. is made and geometric model of these add-on devices are created. These add-on devices are assembled with the baseline model. Steady state CFD simulations are done on the modified car to evaluate the aerodynamic effects of these add-on devices on the car. Later comparison of lap time simulation of the formula student car with and without the add-on devices is done with the help of MATLAB. Aerodynamic performances like: - lift, drag and their coefficients are evaluated for different configuration and design of the add-on devices at different speed of the vehicle. From parametric CFD simulations on formula student car attached with add-on devices, there is a considerable amount of drag and lift force reduction besides streamlining the airflow across the car. The best possible configuration of these add-on devices is obtained from these CFD simulations and also use of these add-on devices have shown an improvement in performance of the car which can be compared by various lap time simulations of the car. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20performance" title="aerodynamic performance">aerodynamic performance</a>, <a href="https://publications.waset.org/abstracts/search?q=front%20wing" title=" front wing"> front wing</a>, <a href="https://publications.waset.org/abstracts/search?q=laptime%20simulation" title=" laptime simulation"> laptime simulation</a>, <a href="https://publications.waset.org/abstracts/search?q=t-wing" title=" t-wing"> t-wing</a> </p> <a href="https://publications.waset.org/abstracts/78638/formula-student-car-design-analysis-and-lap-time-simulation" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/78638.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">197</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">13036</span> Aerodynamic Coefficients Prediction from Minimum Computation Combinations Using OpenVSP Software</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Marine%20Segui">Marine Segui</a>, <a href="https://publications.waset.org/abstracts/search?q=Ruxandra%20Mihaela%20Botez"> Ruxandra Mihaela Botez</a> </p> <p class="card-text"><strong>Abstract:</strong></p> OpenVSP is an aerodynamic solver developed by National Aeronautics and Space Administration (NASA) that allows building a reliable model of an aircraft. This software performs an aerodynamic simulation according to the angle of attack of the aircraft makes between the incoming airstream, and its speed. A reliable aerodynamic model of the Cessna Citation X was designed but it required a lot of computation time. As a consequence, a prediction method was established that allowed predicting lift and drag coefficients for all Mach numbers and for all angles of attack, exclusively for stall conditions, from a computation of three angles of attack and only one Mach number. Aerodynamic coefficients given by the prediction method for a Cessna Citation X model were finally compared with aerodynamics coefficients obtained using a complete OpenVSP study. <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=coefficient" title=" coefficient"> coefficient</a>, <a href="https://publications.waset.org/abstracts/search?q=cruise" title=" cruise"> cruise</a>, <a href="https://publications.waset.org/abstracts/search?q=improving" title=" improving"> improving</a>, <a href="https://publications.waset.org/abstracts/search?q=longitudinal" title=" longitudinal"> longitudinal</a>, <a href="https://publications.waset.org/abstracts/search?q=openVSP" title=" openVSP"> openVSP</a>, <a href="https://publications.waset.org/abstracts/search?q=solver" title=" solver"> solver</a>, <a href="https://publications.waset.org/abstracts/search?q=time" title=" time"> time</a> </p> <a href="https://publications.waset.org/abstracts/85268/aerodynamic-coefficients-prediction-from-minimum-computation-combinations-using-openvsp-software" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/85268.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">235</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">13035</span> Aerodynamic Design of a Light Long Range Blended Wing Body Unmanned Vehicle</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Halison%20da%20Silva%20Pereira">Halison da Silva Pereira</a>, <a href="https://publications.waset.org/abstracts/search?q=Ciro%20Sobrinho%20Campolina%20Martins"> Ciro Sobrinho Campolina Martins</a>, <a href="https://publications.waset.org/abstracts/search?q=Vitor%20Mainenti%20Leal%20Lopes"> Vitor Mainenti Leal Lopes</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Long range performance is a goal for aircraft configuration optimization. Blended Wing Body (BWB) is presented in many works of literature as the most aerodynamically efficient design for a fixed-wing aircraft. Because of its high weight to thrust ratio, BWB is the ideal configuration for many Unmanned Aerial Vehicle (UAV) missions on geomatics applications. In this work, a BWB aerodynamic design for typical light geomatics payload is presented. Aerodynamic non-dimensional coefficients are predicted using low Reynolds number computational techniques (3D Panel Method) and wing parameters like aspect ratio, taper ratio, wing twist and sweep are optimized for high cruise performance and flight quality. The methodology of this work is a summary of tailless aircraft wing design and its application, with appropriate computational schemes, to light UAV subjected to low Reynolds number flows leads to conclusions like the higher performance and flight quality of thicker airfoils in the airframe body and the benefits of using aerodynamic twist rather than just geometric. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=blended%20wing%20body" title="blended wing body">blended wing body</a>, <a href="https://publications.waset.org/abstracts/search?q=low%20Reynolds%20number" title=" low Reynolds number"> low Reynolds number</a>, <a href="https://publications.waset.org/abstracts/search?q=panel%20method" title=" panel method"> panel method</a>, <a href="https://publications.waset.org/abstracts/search?q=UAV" title=" UAV"> UAV</a> </p> <a href="https://publications.waset.org/abstracts/33948/aerodynamic-design-of-a-light-long-range-blended-wing-body-unmanned-vehicle" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/33948.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">586</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">13034</span> A Design Method for Wind Turbine Blade to Have Uniform Strength and Optimum Power Generation Performance</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Pengfei%20Liu">Pengfei Liu</a>, <a href="https://publications.waset.org/abstracts/search?q=Yiyi%20Xu"> Yiyi Xu</a> </p> <p class="card-text"><strong>Abstract:</strong></p> There have been substantial incidents of wind turbine blade fractures and failures due to the lack of systematic blade strength design method incorporated with the aerodynamic forces and power generation efficiency. This research was to develop a methodology and procedure for the wind turbine rotor blade strength taking into account the strength, integration, and aerodynamic performance in terms of power generation efficiency. The wind turbine blade designed using this method and procedure will have a uniform strength across the span to save unnecessary thickness in many blade radial locations and yet to maintain the optimum power generation performance. A turbine rotor code, taking into account both aerodynamic and structural properties, was developed. An existing wind turbine blade was used as an example. For a condition of extreme wind speed of 100 km per hour, the design reduced about 19% of material usage while maintaining the optimum power regeneration efficiency. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=renewable%20energy" title="renewable energy">renewable energy</a>, <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=turbine%20blade%20strength" title=" turbine blade strength"> turbine blade strength</a>, <a href="https://publications.waset.org/abstracts/search?q=aerodynamics-strength%20coupled%20optimization" title=" aerodynamics-strength coupled optimization"> aerodynamics-strength coupled optimization</a> </p> <a href="https://publications.waset.org/abstracts/120082/a-design-method-for-wind-turbine-blade-to-have-uniform-strength-and-optimum-power-generation-performance" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/120082.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">179</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">13033</span> Nonlinear Aerodynamic Parameter Estimation of a Supersonic Air to Air Missile by Using Artificial Neural Networks</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Tugba%20Bayoglu">Tugba Bayoglu</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Aerodynamic parameter estimation is very crucial in missile design phase, since accurate high fidelity aerodynamic model is required for designing high performance and robust control system, developing high fidelity flight simulations and verification of computational and wind tunnel test results. However, in literature, there is not enough missile aerodynamic parameter identification study for three main reasons: (1) most air to air missiles cannot fly with constant speed, (2) missile flight test number and flight duration are much less than that of fixed wing aircraft, (3) variation of the missile aerodynamic parameters with respect to Mach number is higher than that of fixed wing aircraft. In addition to these challenges, identification of aerodynamic parameters for high wind angles by using classical estimation techniques brings another difficulty in the estimation process. The reason for this, most of the estimation techniques require employing polynomials or splines to model the behavior of the aerodynamics. However, for the missiles with a large variation of aerodynamic parameters with respect to flight variables, the order of the proposed model increases, which brings computational burden and complexity. Therefore, in this study, it is aimed to solve nonlinear aerodynamic parameter identification problem for a supersonic air to air missile by using Artificial Neural Networks. The method proposed will be tested by using simulated data which will be generated with a six degree of freedom missile model, involving a nonlinear aerodynamic database. The data will be corrupted by adding noise to the measurement model. Then, by using the flight variables and measurements, the parameters will be estimated. Finally, the prediction accuracy will be investigated. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=air%20to%20air%20missile" title="air to air missile">air to air missile</a>, <a href="https://publications.waset.org/abstracts/search?q=artificial%20neural%20networks" title=" artificial neural networks"> artificial neural networks</a>, <a href="https://publications.waset.org/abstracts/search?q=open%20loop%20simulation" title=" open loop simulation"> open loop simulation</a>, <a href="https://publications.waset.org/abstracts/search?q=parameter%20identification" title=" parameter identification"> parameter identification</a> </p> <a href="https://publications.waset.org/abstracts/72976/nonlinear-aerodynamic-parameter-estimation-of-a-supersonic-air-to-air-missile-by-using-artificial-neural-networks" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/72976.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">13032</span> Aerodynamic Brake Study of Reducing Braking Distance for High-Speed Trains</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Phatthara%20Surachon">Phatthara Surachon</a>, <a href="https://publications.waset.org/abstracts/search?q=Tosaphol%20Ratniyomchai"> Tosaphol Ratniyomchai</a>, <a href="https://publications.waset.org/abstracts/search?q=Thanatchai%20Kulworawanichpong"> Thanatchai Kulworawanichpong</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper presents an aerodynamic brake study of reducing braking distance for high-speed trains (HST) using aerodynamic brakes as inspiration from the applications on the commercial aircraft wings. In case of emergency, both braking distance and stopping time are longer than the usual situation. Therefore, the passenger safety and the HST driving control management are definitely obtained by reducing the time and distance of train braking during emergency situation. Due to the limited study and implementation of the aerodynamic brake in HST, the possibility in use and the effectiveness of the aerodynamic brake to the train dynamic movement during braking are analyzed and considered. Regarding the aircraft’s flaps that applied in the HST, the areas of the aerodynamic brake acted as an additional drag force during train braking are able to vary depending on the operating angle and the required dynamic braking force. The HST with a varying speed of 200 km/h to 350 km/h is taken as a case study of this paper. The results show that the stopping time and the brake distance are effectively reduced by the aerodynamic brakes. The mechanical brake and its maintenance are effectively getting this benefit by extending its lifetime for longer use. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=high-speed%20train" title="high-speed train">high-speed train</a>, <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20brake" title=" aerodynamic brake"> aerodynamic brake</a>, <a href="https://publications.waset.org/abstracts/search?q=brake%20distance" title=" brake distance"> brake distance</a>, <a href="https://publications.waset.org/abstracts/search?q=drag%20force" title=" drag force "> drag force </a> </p> <a href="https://publications.waset.org/abstracts/122559/aerodynamic-brake-study-of-reducing-braking-distance-for-high-speed-trains" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/122559.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">199</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">13031</span> Multi-Objective Optimization of an Aerodynamic Feeding System Using Genetic Algorithm</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Jan%20Busch">Jan Busch</a>, <a href="https://publications.waset.org/abstracts/search?q=Peter%20Nyhuis"> Peter Nyhuis</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Considering the challenges of short product life cycles and growing variant diversity, cost minimization and manufacturing flexibility increasingly gain importance to maintain a competitive edge in today’s global and dynamic markets. In this context, an aerodynamic part feeding system for high-speed industrial assembly applications has been developed at the Institute of Production Systems and Logistics (IFA), Leibniz Universitaet Hannover. The aerodynamic part feeding system outperforms conventional systems with respect to its process safety, reliability, and operating speed. In this paper, a multi-objective optimisation of the aerodynamic feeding system regarding the orientation rate, the feeding velocity and the required nozzle pressure is presented. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20feeding%20system" title="aerodynamic feeding system">aerodynamic feeding system</a>, <a href="https://publications.waset.org/abstracts/search?q=genetic%20algorithm" title=" genetic algorithm"> genetic algorithm</a>, <a href="https://publications.waset.org/abstracts/search?q=multi-objective%20optimization" title=" multi-objective optimization"> multi-objective optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=workpiece%20orientation" title=" workpiece orientation"> workpiece orientation</a> </p> <a href="https://publications.waset.org/abstracts/34640/multi-objective-optimization-of-an-aerodynamic-feeding-system-using-genetic-algorithm" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/34640.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">577</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">13030</span> Development of a Self-Retractable Front Spoilers Suitable for Indian Road Conditions to Reduce Aerodynamic Drag</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=G.%20Sivaraj">G. Sivaraj</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20M.%20Parammasivam"> K. M. Parammasivam</a>, <a href="https://publications.waset.org/abstracts/search?q=R.%20Veeramanikandan"> R. Veeramanikandan</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Nithish"> S. Nithish</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Reduction of ground clearance or (ride height) is a vital factor in minimizing aerodynamic drag force and improving vehicle performance. But in India, minimization of ground clearance is limited because of the road conditions. Due to this problem, reduction of aerodynamic drag and performance are not fully improved. In this view, this paper deals with the development of self-retractable front spoilers which are most suitable for Indian road conditions. These retractable spoilers are fitted in the front portion of the car and in speed below 60 km/hr these spoilers are in retracted positions. But, when the car crosses a speed above 60 km/hr, using electronic circuit the spoilers are activated. Thus, using this technique aerodynamic performance can be improved at a speed above 60 km/hr. Also, when the car speed is reduced below the 60 km/hr mark, the front spoiler are retracted which makes it as a normal car. This is because, in Indian roads, speed breakers are installed to cut off speed at particular places. Thus, in these circumstances there are chances of damaging front spoilers. Since, when the driver sees the speed breaker, he will automatically apply break to prevent damage, at this time using electronic circuit the front spoiler is retracted. However, accidentally when the driver fails to apply brakes there are chances for the front spoilers to get a hit. But as the front spoilers are made of Kevlar composite, it can withstand high impact loads and using a spring mechanism the spoilers are retracted immediately. By using CFD analysis and low-speed wind tunnel testing drag coefficient of the 1:10 scaled car model with and without self-retractable spoilers are calculated and validated. Also, using wind tunnel, proper working of self-retractable at car speed below and above 60 km/hr are validated. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20drag" title="aerodynamic drag">aerodynamic drag</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD%20analysis" title=" CFD analysis"> CFD analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=kevlar%20composite" title=" kevlar composite"> kevlar composite</a>, <a href="https://publications.waset.org/abstracts/search?q=self-retractable%20spoilers" title=" self-retractable spoilers"> self-retractable spoilers</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20tunnel" title=" wind tunnel"> wind tunnel</a> </p> <a href="https://publications.waset.org/abstracts/39491/development-of-a-self-retractable-front-spoilers-suitable-for-indian-road-conditions-to-reduce-aerodynamic-drag" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/39491.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">13029</span> Multi-Fidelity Fluid-Structure Interaction Analysis of a Membrane Wing</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=M.%20Saeedi">M. Saeedi</a>, <a href="https://publications.waset.org/abstracts/search?q=R.%20Wuchner"> R. Wuchner</a>, <a href="https://publications.waset.org/abstracts/search?q=K.-U.%20Bletzinger"> K.-U. Bletzinger</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In order to study the aerodynamic performance of a semi-flexible membrane wing, Fluid-Structure Interaction simulations have been performed. The fluid problem has been modeled using two different approaches which are the numerical solution of the Navier-Stokes equations and the vortex panel method. Nonlinear analysis of the structural problem is performed using the Finite Element Method. Comparison between the two fluid solvers has been made. Aerodynamic performance of the wing is discussed regarding its lift and drag coefficients and they are compared with those of the equivalent rigid wing. <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=FSI" title=" FSI"> FSI</a>, <a href="https://publications.waset.org/abstracts/search?q=Membrane%20wing" title=" Membrane wing"> Membrane wing</a>, <a href="https://publications.waset.org/abstracts/search?q=Vortex%20panel%20method" title=" Vortex panel method"> Vortex panel method</a> </p> <a href="https://publications.waset.org/abstracts/17424/multi-fidelity-fluid-structure-interaction-analysis-of-a-membrane-wing" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/17424.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">486</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">13028</span> Control Flow around NACA 4415 Airfoil Using Slot and Injection</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Imine%20Zakaria">Imine Zakaria</a>, <a href="https://publications.waset.org/abstracts/search?q=Meftah%20Sidi%20Mohamed%20El%20Amine"> Meftah Sidi Mohamed El Amine</a> </p> <p class="card-text"><strong>Abstract:</strong></p> One of the most vital aerodynamic organs of a flying machine is the wing, which allows it to fly in the air efficiently. The flow around the wing is very sensitive to changes in the angle of attack. Beyond a value, there is a phenomenon of the boundary layer separation on the upper surface, which causes instability and total degradation of aerodynamic performance called a stall. However, controlling flow around an airfoil has become a researcher concern in the aeronautics field. There are two techniques for controlling flow around a wing to improve its aerodynamic performance: passive and active controls. Blowing and suction are among the active techniques that control the boundary layer separation around an airfoil. Their objective is to give energy to the air particles in the boundary layer separation zones and to create vortex structures that will homogenize the velocity near the wall and allow control. Blowing and suction have long been used as flow control actuators around obstacles. In 1904 Prandtl applied a permanent blowing to a cylinder to delay the boundary layer separation. In the present study, several numerical investigations have been developed to predict a turbulent flow around an aerodynamic profile. CFD code was used for several angles of attack in order to validate the present work with that of the literature in the case of a clean profile. The variation of the lift coefficient CL with the momentum coefficient <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=control%20flow" title=" control flow"> control flow</a>, <a href="https://publications.waset.org/abstracts/search?q=lift" title=" lift"> lift</a>, <a href="https://publications.waset.org/abstracts/search?q=slot" title=" slot"> slot</a> </p> <a href="https://publications.waset.org/abstracts/133748/control-flow-around-naca-4415-airfoil-using-slot-and-injection" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/133748.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">197</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">13027</span> Aerodynamic Analysis of Multiple Winglets for Aircrafts</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=S.%20Pooja%20Pragati">S. Pooja Pragati</a>, <a href="https://publications.waset.org/abstracts/search?q=B.%20Sudarsan"> B. Sudarsan</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Raj%20Kumar"> S. Raj Kumar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper provides a practical design of a new concept of massive Induced Drag reductions of stream vise staggered multiple winglets. It is designed to provide an optimum performance of a winglet from conventional designs. In preparing for a mechanical design, aspects such as shape, dimensions are analyzed to yield a huge amount of reduction in fuel consumption and increased performance. Owing to its simplicity of application and effectiveness we believe that it will enable us to consider its enhanced version for the grid effect of the staggered multiple winglets on the deflected mass flow of the wing system. The objective of the analysis were to compare the aerodynamic characteristics of two winglet configuration and to investigate the performance of two winglets shape simulated at selected cant angle of 0,45,60 degree. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=multiple%20winglets" title="multiple winglets">multiple winglets</a>, <a href="https://publications.waset.org/abstracts/search?q=induced%20drag" title=" induced drag"> induced drag</a>, <a href="https://publications.waset.org/abstracts/search?q=aerodynamics%20analysis" title=" aerodynamics analysis"> aerodynamics analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=low%20speed%20aircrafts" title=" low speed aircrafts"> low speed aircrafts</a> </p> <a href="https://publications.waset.org/abstracts/29408/aerodynamic-analysis-of-multiple-winglets-for-aircrafts" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/29408.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">480</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">13026</span> Design and Validation of an Aerodynamic Model of the Cessna Citation X Horizontal Stabilizer Using both OpenVSP and Digital Datcom</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Marine%20Segui">Marine Segui</a>, <a href="https://publications.waset.org/abstracts/search?q=Matthieu%20Mantilla"> Matthieu Mantilla</a>, <a href="https://publications.waset.org/abstracts/search?q=Ruxandra%20Mihaela%20Botez"> Ruxandra Mihaela Botez</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This research is the part of a major project at the Research Laboratory in Active Controls, Avionics and Aeroservoelasticity (LARCASE) aiming to improve a Cessna Citation X aircraft cruise performance with an application of the morphing wing technology on its horizontal tail. However, the horizontal stabilizer of the Cessna Citation X turns around its span axis with an angle between -8 and 2 degrees. Within this range, the horizontal stabilizer generates certainly some unwanted drag. To cancel this drag, the LARCASE proposes to trim the aircraft with a horizontal stabilizer equipped by a morphing wing technology. This technology aims to optimize aerodynamic performances by changing the conventional horizontal tail shape during the flight. As a consequence, this technology will be able to generate enough lift on the horizontal tail to balance the aircraft without an unwanted drag generation. To conduct this project, an accurate aerodynamic model of the horizontal tail is firstly required. This aerodynamic model will finally allow precise comparison between a conventional horizontal tail and a morphed horizontal tail results. This paper presents how this aerodynamic model was designed. In this way, it shows how the 2D geometry of the horizontal tail was collected and how the unknown airfoil&rsquo;s shape of the horizontal tail has been recovered. Finally, the complete horizontal tail airfoil shape was found and a comparison between aerodynamic polar of the real horizontal tail and the horizontal tail found in this paper shows a maximum difference of 0.04 on the lift or the drag coefficient which is very good. Aerodynamic polar data of the aircraft horizontal tail are obtained from the CAE Inc. level D research aircraft flight simulator of the Cessna Citation X. <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=Cessna" title=" Cessna"> Cessna</a>, <a href="https://publications.waset.org/abstracts/search?q=citation" title=" citation"> citation</a>, <a href="https://publications.waset.org/abstracts/search?q=coefficient" title=" coefficient"> coefficient</a>, <a href="https://publications.waset.org/abstracts/search?q=Datcom" title=" Datcom"> Datcom</a>, <a href="https://publications.waset.org/abstracts/search?q=drag" title=" drag"> drag</a>, <a href="https://publications.waset.org/abstracts/search?q=lift" title=" lift"> lift</a>, <a href="https://publications.waset.org/abstracts/search?q=longitudinal" title=" longitudinal"> longitudinal</a>, <a href="https://publications.waset.org/abstracts/search?q=model" title=" model"> model</a>, <a href="https://publications.waset.org/abstracts/search?q=OpenVSP" title=" OpenVSP"> OpenVSP</a> </p> <a href="https://publications.waset.org/abstracts/84863/design-and-validation-of-an-aerodynamic-model-of-the-cessna-citation-x-horizontal-stabilizer-using-both-openvsp-and-digital-datcom" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/84863.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">374</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">13025</span> Enhancing Aerodynamic Performance of Savonius Vertical Axis Turbine Used with Triboelectric Generator</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Bhavesh%20Dadhich">Bhavesh Dadhich</a>, <a href="https://publications.waset.org/abstracts/search?q=Fenil%20Bamnoliya"> Fenil Bamnoliya</a>, <a href="https://publications.waset.org/abstracts/search?q=Akshita%20Swaminathan"> Akshita Swaminathan</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This project aims to design a system to generate energy from flowing wind due to the motion of a vehicle on the road or from the flow of wind in compact areas to utilize the wasteful energy into a useful one. It is envisaged through a design and aerodynamic performance improvement of a Savonius vertical axis wind turbine rotor and used in an integrated system with a Triboelectric Nanogenerator (TENG) that can generate a good amount of electrical energy. Aerodynamic calculations are performed numerically using Computational Fluid Dynamics software, and TENG's performance is evaluated analytically. The Turbine's coefficient of power is validated with published results for an inlet velocity of 7 m/s with a Tip Speed Ratio of 0.75 and found to reasonably agree with that of experiment results. The baseline design is modified with a new blade arc angle and rotor position angle based on the recommended parameter ranges suggested by previous researchers. Simulations have been performed for different T.S.R. values ranging from 0.25 to 1.5 with an interval of 0.25 with two applicable free stream velocities of 5 m/s and 7m/s. Finally, the newly designed VAWT CFD performance results are used as input for the analytical performance prediction of the triboelectric nanogenerator. The results show that this approach could be feasible and useful for small power source applications. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=savonius%20turbine" title="savonius turbine">savonius turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=power" title=" power"> power</a>, <a href="https://publications.waset.org/abstracts/search?q=overlap%20ratio" title=" overlap ratio"> overlap ratio</a>, <a href="https://publications.waset.org/abstracts/search?q=tip%20speed%20ratio" title=" tip speed ratio"> tip speed ratio</a>, <a href="https://publications.waset.org/abstracts/search?q=TENG" title=" TENG"> TENG</a> </p> <a href="https://publications.waset.org/abstracts/148462/enhancing-aerodynamic-performance-of-savonius-vertical-axis-turbine-used-with-triboelectric-generator" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/148462.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">122</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">13024</span> Reduction of Aerodynamic Drag Using Vortex Generators</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Siddharth%20Ojha">Siddharth Ojha</a>, <a href="https://publications.waset.org/abstracts/search?q=Varun%20Dua"> Varun Dua</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Classified as one of the most important reasons of aerodynamic drag in the sedan automobiles is the fluid flow separation near the vehicle’s rear end. To retard the separation of flow, bump-shaped vortex generators are being tested for its implementation to the roof end of a sedan vehicle. Frequently used in the aircrafts to prevent the separation of fluid flow, vortex generators themselves produce drag, but they also substantially reduce drag by preventing flow separation at the downstream. The net effects of vortex generators can be calculated by summing the positive and negative impacts and effects. Since this effect depends on dimensions and geometry of vortex generators, those present on the vehicle roof are optimized for maximum efficiency and performance. The model was tested through ANSYS CFD analysis and modeling. The model was tested in the wind tunnel for observing it’s properties such as aerodynamic drag and flow separation and a major time lag was gained by employing vortex generators in the scaled model. Major conclusions which were recorded during the analysis were a substantial 24% reduction in the aerodynamic drag and 14% increase in the efficiency of the sedan automobile as the flow separation from the surface is delayed. This paper presents the results of optimization, the effect of vortex generators in the flow field and the mechanism by which these effects occur and are regulated. <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=aerodynamic%20devices" title=" aerodynamic devices"> aerodynamic devices</a>, <a href="https://publications.waset.org/abstracts/search?q=body" title=" body"> body</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=flow%20visualization" title=" flow visualization"> flow visualization</a> </p> <a href="https://publications.waset.org/abstracts/76172/reduction-of-aerodynamic-drag-using-vortex-generators" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/76172.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">223</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">13023</span> Improvement of the Aerodynamic Behaviour of a Land Rover Discovery 4 in Turbulent Flow Using Computational Fluid Dynamics (CFD)</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ahmed%20Al-Saadi">Ahmed Al-Saadi</a>, <a href="https://publications.waset.org/abstracts/search?q=Ali%20Hassanpour"> Ali Hassanpour</a>, <a href="https://publications.waset.org/abstracts/search?q=Tariq%20Mahmud"> Tariq Mahmud</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The main objective of this study is to investigate ways to reduce the aerodynamic drag coefficient and to increase the stability of the full-size Sport Utility Vehicle using three-dimensional Computational Fluid Dynamics (CFD) simulation. The baseline model in the simulation was the Land Rover Discovery 4. Many aerodynamic devices and external design modifications were used in this study. These reduction aerodynamic techniques were tested individually or in combination to get the best design. All new models have the same capacity and comfort of the baseline model. Uniform freestream velocity of the air at inlet ranging from 28 m/s to 40 m/s was used. ANSYS Fluent software (version 16.0) was used to simulate all models. The drag coefficient obtained from the ANSYS Fluent for the baseline model was validated with experimental data. It is found that the use of modern aerodynamic add-on devices and modifications has a significant effect in reducing the aerodynamic drag coefficient. <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=RANS" title=" RANS"> RANS</a>, <a href="https://publications.waset.org/abstracts/search?q=sport%20utility%20vehicle" title=" sport utility vehicle"> sport utility vehicle</a>, <a href="https://publications.waset.org/abstracts/search?q=turbulent%20flow" title=" turbulent flow"> turbulent flow</a> </p> <a href="https://publications.waset.org/abstracts/63731/improvement-of-the-aerodynamic-behaviour-of-a-land-rover-discovery-4-in-turbulent-flow-using-computational-fluid-dynamics-cfd" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/63731.pdf" target="_blank" class="btn btn-primary 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