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Accession Number:
AD0670189
Title:
ACCELERATION OF A HYPERSONIC BOUNDARY LAYER APPROACHING A CORNER.
Corporate Author:
MICHIGAN UNIV ANN ARBOR INST OF SCIENCE AND TECHNOLOGY
Report Date:
1968-05-01
Abstract:
An asymptotic description of the acceleration of a laminar hypersonic boundary layer approaching a sharp corner is obtained. The description assumes small interaction with the outer inviscid flow. Viscous forces are neglected except in a thin sublayer. The initial part of the expansion takes place over a distance OM sub e differential, where M sub e is the external Mach number, and differential is the boundary-layer thickness. Here the transverse pressure gradient is small, and a solution can be obtained analytically. Within a distance Odifferential from the corner, the effect of streamline curvature is essential, and a numerical solution is obtained by the method of integral relations for a single strip. The solution for surface pressure is compared with experimental results for a particular case,and an approximate velocity profile at the corner is calculated. Possibilities for improving the accuracy of the calculation, both by refining the numerical procedure and by including higher order effects, are considered. Author
Descriptive Note:
Report of BAMIRAC,
Supplementary Note:
Doctoral thesis.
Pages:
0098
Contract Number:
DAHC15-67-C-0062
File Size:
0.00MB
