When velocity of flight approaches that of sound, considerable increase of drag occurs due to boundary layer separation caused by shock waves; experiments showed that drag increase may be considerably reduced by suction of boundary layer. English translation from ZWB Forschungsbericht n 1424 July 1 1941.
Drag reduction by suction of boundary layer separated behind shock wave formation at high Mach numbers
Nat Advisory Committee Aeronautics -- Tech Memo
1947
13 pages
5 Supp Sheets
Report
Englisch
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Shock-Wave/Boundary-Layer Interactions in High-Mach-Number Flows
British Library Online Contents | 1996
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