Actions for Effects of Nose Bluntness on Stability of Hypersonic Boundary Layers over Blunt Cone

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Effects of Nose Bluntness on Stability of Hypersonic Boundary Layers over Blunt Cone

Author
Kandil, O. A.
Published
June 27, 2007.
Physical Description
1 electronic document
Additional Creators
Balakumar, P. and Kara, K.
Online Version

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Summary
Receptivity 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.
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Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 20070028873.
37th AIAA Fluid Dynamics Conference and Exhibit; 25-28 Jun. 2007; Miami, FL; United States.
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Copyright, Distribution as joint owner in the copyright.
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