Streamline Swallowing by Laminar Boundary Layers in Hypersonic Flow
Final rept. Sep 1969-Jun 1970
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Flow over a cold-wall, 22.5-deg asymptotic half-angle hyperboloid at a free-stream Mach number of 10 and free-stream Reynolds numbers based on nose radius of 400, 4000, and 40,000 is considered. Numerical results from a streamline-swallowing, nonsimilar, laminar, boundary-layer analysis are compared with results from classical boundary-layer theory, second-order boundary-layer theory, and a fully viscous shock-layer analysis the results of the latter are used as a standard of comparison. The major improvement effected by the streamline-swallowing analysis is the inclusion of shock curvature effects on the boundary conditions applied along the outer edge of the boundary layer. Results from the streamline-swallowing boundary-layer analysis agree better with the results of the fully viscous shock-layer analysis, than the classical boundary layer and the second-order boundary-layer results. Reasons for the success of one method and the failure of others are discussed.
- Fluid Mechanics
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