Numerical simulation of the peculiar subsonic flow-field about the VFE-2 delta wing with rounded leading edge |
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| Authors: | Willy Fritz |
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| Institution: | 1. Institute of Aeroelasticity, DLR (German Aerospace Center), Bunsenstrasse 10, 37073 Goettingen, Germany;2. Department for Structural Dynamics and Aeroelasticity, Airbus Defence and Space, Rechliner Strasse, 85077 Manching, Germany;1. Turkish Aerospace Industries, Inc., Aerodynamics Chief Engineer at TF-X Project, Ankara 06980, Turkey;2. Mechanical Engineering Department, Middle East Technical University, Ankara 06800, Turkey;1. Nangia Aero Research, Bristol, UK;2. High Performance Computing Research Center, U.S. Air Force Academy, CO 80840, USA;3. Netherlands Aerospace Centre NLR, Amsterdam, the Netherlands;4. Department of Aeronautics, U.S. Air Force Academy, CO 80840, USA;1. School of Aerospace Engineering, Tsinghua University, Beijing, 100084, China;2. China Aerodynamics Research and Development Center, Mianyang, 621000, China |
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| Abstract: | The Second International Vortex Flow Experiment provided a variety of experimental data for a 65° swept delta wing sharp and blunt leading edges. Flow details including forces and moments, surface pressures, Pressure Sensitive Paint measurements, and off-surface flow variables from Particle Image Velocimetry were made available for comparisons with computational simulations. This paper concentrates on some typical problems of delta wings with rounded leading edges at subsonic speed: the prediction of the main leading edge separation, the generation of the second inner vortex, the effect of transition, and Reynolds number effects. |
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