Accession Number:

AD0719748

Title:

Streamline Swallowing by Laminar Boundary Layers in Hypersonic Flow

Descriptive Note:

Final rept. Sep 1969-Jun 1970

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1971-03-01

Pagination or Media Count:

44.0

Abstract:

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.

Subject Categories:

  • Fluid Mechanics
  • Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE