Compression shocks which lead from supersonic to subsonic velocity causeflow to separate on impact on rigid wall; such shocks appear at bodies with circular symmetry of wing profiles on locally exceeding sonic velocity, and in Laval nozzles with too high back pressure; form of compression shocks observed therein is investigated. English translation from (ZWB) Deutsche Luftfahrtforschung, Forschungsbericht n 1850, Aug 12 1943.
Compression shocks of detached flow
Nat Advisory Committee Aeronautics -- Tech Memo
1947
15 pages
10 Supp Sheets
Report
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Compression shocks of detached flow
TIBKAT | 1947
|Review of analytical methods for treatment of flows with detached shocks
Engineering Index Backfile | 1949
|