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Effects of Nose Bluntness on Stability of Hypersonic Boundary Layers over Blunt ConeReceptivity and stability of hypersonic boundary layers are numerically investigated for boundary layer flows over a 5-degree straight cone at a free-stream Mach number of 6.0. To compute the shock and the interaction of shock with the instability waves, we solve the Navier-Stokes equations in axisymmetric coordinates. The governing equations are solved using the 5th-order accurate weighted essentially non-oscillatory (WENO) scheme for space discretization and using third-order total-variation-diminishing (TVD) Runge-Kutta scheme for time integration. After the mean flow field is computed, disturbances are introduced at the upstream end of the computational domain. Generation of instability waves from leading edge region and receptivity of boundary layer to slow acoustic waves are investigated. Computations are performed for a cone with nose radii of 0.001, 0.05 and 0.10 inches that give Reynolds numbers based on the nose radii ranging from 650 to 130,000. The linear stability results showed that the bluntness has a strong stabilizing effect on the stability of axisymmetric boundary layers. The transition Reynolds number for a cone with the nose Reynolds number of 65,000 is increased by a factor of 1.82 compared to that for a sharp cone. The receptivity coefficient for a sharp cone is about 4.23 and it is very small, approx.10(exp -3), for large bluntness.
Document ID
20070028873
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Kara, K.
(Old Dominion Univ. Norfolk, VA, United States)
Balakumar, P.
(NASA Langley Research Center Hampton, VA, United States)
Kandil, O. A.
(Old Dominion Univ. Norfolk, VA, United States)
Date Acquired
August 23, 2013
Publication Date
June 27, 2007
Subject Category
Aerodynamics
Meeting Information
Meeting: 37th AIAA Fluid Dynamics Conference and Exhibit
Location: Miami, FL
Country: United States
Start Date: June 25, 2007
End Date: June 28, 2007
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 984754
Distribution Limits
Public
Copyright
Public Use Permitted.
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