Self-Excited Supersonic Cavity Flow Instabilities as Aerodynamic Noise Sources
نویسندگان
چکیده
منابع مشابه
Shock Motion and Flow Instabilities in Supersonic Nozzle Flow Separation
This study evaluates the role of shock wave motion on the instability of the plume exiting an over-expanded, convergent-divergent nozzle. An array of wall pressure transducers was used to track the position of the shock in time, and a Pitot probe was used to obtain simultaneous measurement of the total pressure fluctuations at various points in the jet that emerges from the separation shock. An...
متن کاملDesign-Oriented Aerodynamic Analysis for Supersonic Laminar Flow Wings
The computation of boundary layer properties and laminar-to-turbulent transition location is a very complex problem, generally not undertaken in the context of aircraft design. Yet if an aircraft is to exploit the advantages of laminar flow and proper trade-offs between inviscid drag, structural weight, and skin friction are to be made, this is just what must be done. This paper summarizes a de...
متن کاملAn Aerodynamic Design Method for Supersonic Natural Laminar Flow Aircraft
The computation of boundary-layer properties and laminar-to-turbulent transition location is a complex problem generally not undertaken in the context of aircraft design. Yet this is just what must be done if an aircraft designer is to exploit the advantages of laminar flow while making the proper trade-offs between inviscid drag, structural weight and skin friction. To facilitate this process,...
متن کاملHydroxyl tagging velocimetry in a supersonic flow over a cavity.
Hydroxyl tagging velocimetry (HTV) measurements of velocity were made in a Mach 2 (M 2) flow with a wall cavity. In the HTV method, ArF excimer laser (193 nm) beams pass through a humid gas and dissociate H2O into H + OH to form a tagging grid of OH molecules. In this study, a 7 x 7 grid of hydroxyl (OH) molecules is tracked by planar laser-induced fluorescence. The grid motion over a fixed tim...
متن کاملDetached Eddy Simulations of Supersonic Flow over Cavity
Detached Eddy Simulations are performed for unsteady three-dimensional supersonic turbulent flow over an open L/D = 5 cavity at free-stream Mach number of 1.19. Numerical results are obtained from the explicit solution and Shear-Stress-Transport based simulations using the 3 order Roe scheme. Computational results are presented for the unsteady vortex and shock structures. The acoustic response...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: International Journal of Aeroacoustics
سال: 2006
ISSN: 1475-472X,2048-4003
DOI: 10.1260/147547206779379921