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.
Reynolds Number Effects on the Shock Wave-Turbulent Boundary Layer Interaction at Transonic Speeds
1973
17 pages
Report
Keine Angabe
Englisch
Fluid Mechanics , Turbulent boundary layer , Shock waves , Interactions , Transonic flow , Two dimensional flow , Supersonic nozzles , Pressure distribution , Airfoils , Surfaces , Pitot tubes , Static pressure , Skin friction , Flow separation , Flow visualization , Schlieren photography , Flow fields , Mach number , Reynolds number , Ludwieg tubes
A normal shock-wave turbulent boundary-layer interaction at transonic speeds
Tema Archiv | 1976
|