A Ludwieg tube experiment is described in which the pertinent features of the shock wave-boundary layer interaction on an airfoil are simulated with a two-dimensional flat plate in a supersonic nozzle. The nozzle is modified to impress an airfoil pressure distribution on the flat plate that is typical of a cruising flight condition. A normal shock wave is positioned at a fixed location on the plate, and measurements are made in the vicinity of the shock wave boundary layer interaction zone. (DePo)
Reynolds number effects on the shock wave-turbulent boundary layer interaction at transonic speeds
Wirkung der Reynolds Zahl auf die Wechselwirkung von Schockwellen und turbulenten Grenzschichten bei transsonischen Stroemungen
US Government Reports ; Jul ; 1-17
1973
17 Seiten
Report
Englisch
A normal shock-wave turbulent boundary-layer interaction at transonic speeds
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