Stability of the Low Reynolds Number Compressible Flow Past a NACA0012 Airfoil
| العنوان: | Stability of the Low Reynolds Number Compressible Flow Past a NACA0012 Airfoil |
|---|---|
| المؤلفون: | Jérémie Gressier, Laura Victoria Rolandi, Laurent Joly, Thierry Jardin, Jérôme Fontane |
| المساهمون: | Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Département Aérodynamique Energétique et Propulsion (DAEP), Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO) |
| المصدر: | AIAA Journal AIAA Journal, American Institute of Aeronautics and Astronautics, 2021, pp.0. ⟨10.2514/1.J060792⟩ |
| بيانات النشر: | American Institute of Aeronautics and Astronautics, 2022. |
| سنة النشر: | 2022 |
| مصطلحات موضوعية: | Airfoil, Low-Reynolds, Lift coefficient, Mécanique des fluides, Direct numerical simulation, Aerospace Engineering, 02 engineering and technology, Global stability, Wake, 01 natural sciences, Compressible flow, 010305 fluids & plasmas, [SPI.MECA.MEFL]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Fluids mechanics [physics.class-ph], Physics::Fluid Dynamics, symbols.namesake, 0203 mechanical engineering, Compressible, Incompressible flow, 0103 physical sciences, 020301 aerospace & aeronautics, Reynolds number, Mechanics, symbols, Compressibility, NACA0012, Geology |
| الوصف: | International audience; With stratospheric flight ormartian exploration in perspective, the compressibility influence on thewake dynamics ofa NACA0012 profile is investigated. The unsteady flow past the airfoil at Re = 1000 is characterized using directnumerical simulations for various angles of attack α ∈ [0°; 20°] and Mach numbers up to M∞ = 0.5. Steady flowsobtained using the selective frequency damping (SFD) technique are used as base states for a global linear stabilityanalysis. The influence of both the angle of attack and the Reynolds number on the most amplifiedmode characteristicsis first investigated in the incompressible regime. Then, the compressibility effects in the subcritical regime areconsidered. A stabilizing or a destabilizing effect of compressibility is observed depending on the angle of attack andtheReynolds number. For α < 20°, compressibility has a destabilizing effect close to the critical threshold,which resultsin anearlierHopfbifurcation,whereas increasing theMach number always results in a decrease of the growth rate of themode well above the critical threshold. Finally, the mode frequency decreases with the Mach number. |
| وصف الملف: | application/pdf |
| اللغة: | English |
| تدمد: | 0001-1452 1533-385X |
| URL الوصول: | https://explore.openaire.eu/search/publication?articleId=doi_dedup___::dcc3f507c170130fd5491a0c7ee9d880 https://oatao.univ-toulouse.fr/28348/ |
| حقوق: | OPEN |
| رقم الأكسشن: | edsair.doi.dedup.....dcc3f507c170130fd5491a0c7ee9d880 |
| قاعدة البيانات: | OpenAIRE |
| تدمد: | 00011452 1533385X |
|---|