Location of separation point on surface of body is determined by pressure rise communicated upstream through subcritical base flow; by using moment method of Reeves and Lees, separation-interaction region is joined to near-wake interaction region passing through "throat" downstream of rear stagnation point; viscous flow over blunt body overexpands and goes supercritical; flow is joined to near-wake by means of supercritical-subcritical "jump" upstream of separation, and jump location is determined; application of method and comparison of results.
Laminar boundary-layer separation and near-wake flow for smooth blunt body at supersonic and hypersonic speeds
AIAA J
AIAA Journal ; 5 , n 6
1967
8 pages
Aufsatz (Zeitschrift)
Englisch
© Metadata Copyright Elsevier B. V. All rights reserved.
Near wake of a blunt body at hypersonic speeds
AIAA | 1965
|Near wake of a blunt body at hypersonic speeds
AIAA | 1964
|