Compression Shocks of Detached Flow
Description:
"It is known that compression shocks which lead from supersonic to subsonic velocity cause the flow to separate on impact on a rigid wall. Such shocks appear at bodies with circular symmetry or wing profiles on locally exceeding sonic velocity, and in Laval nozzles with too high a back pressure. The form of the compression shocks observed therein is investigated" (p. 1).
Date:
June 1947
Creator:
Eggink
Item Type:
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Report
Partner:
UNT Libraries Government Documents Department