NASA NTRS · 20050019417
Compression Shocks of Detached Flow
Abstract
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.
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Eggink. 1947-06-01. Compression Shocks of Detached Flow. https://ntrs.nasa.gov/citations/20050019417
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