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Receptivity of Hypersonic Boundary Layers to Acoustic and Vortical DisturbancesBoundary layer receptivity to two-dimensional acoustic disturbances at different incidence angles and to vortical disturbances is investigated by solving the Navier-Stokes equations for Mach 6 flow over a 7deg half-angle sharp-tipped wedge and a cone. Higher order spatial and temporal schemes are employed to obtain the solution. The results show that the instability waves are generated in the leading edge region and that the boundary layer is much more receptive to slow acoustic waves as compared to the fast waves. It is found that the receptivity of the boundary layer on the windward side (with respect to the acoustic forcing) decreases when the incidence angle is increased from 0 to 30 degrees. However, the receptivity coefficient for the leeward side is found to vary relatively weakly with the incidence angle. The maximum receptivity is obtained when the wave incident angle is about 20 degrees. Vortical disturbances also generate unstable second modes, however the receptivity coefficients are smaller than that for the acoustic waves. Vortical disturbances first generate the fast acoustic modes and they switch to the slow mode near the continuous spectrum.
Document ID
20110002882
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Balakamar, P. (NASA Langley Research Center Hampton, VA, United States)
Kegerise, Michael A. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 25, 2013
Publication Date
January 4, 2011
Subject Category
Acoustics
Report/Patent Number
AIAA Paper 2011-0371
NF1676L-11800
Meeting Information
Meeting: 49th AIAA Aerospace Sciences Meeting
Location: Orlando, FL
Country: United States
Start Date: January 4, 2011
End Date: January 7, 2011
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 599489.02.07.07.04.11.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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