Add to ORKGResults are presented of a dimensional study and an experimental investigation of the pressure rise across a shock wave which causes separation of the boundary layer on a flat plate. The experimental part of the investigation was conducted at a Mach number of 3.03 for a Reynolds number range of 2 x 10 (sup) 6 to 19 x 10 (sup) 6. The available experimental data are compared with the predictions of the present study, and the significance of the results obtained is discussed relative to certain practical design problems
A two-dimensional experimental and theoretical investigation has been conducted on an NACA 651-213 a...
This article presents an investigation on a correlation relevant to flow separation during shock wav...
The experimental study of the effect of weak shock waves on the supersonic boundary layer of the fla...
A dimensional study and an experimental investigation have been made on the pressure rise across sho...
The present status of available information relative to the prediction of shock-induced boundary-lay...
A change in flow pattern that was observed as the free-stream Mach number was increased in the vicin...
Measurements are presented at Mach numbers from about 1.3 to 1.5 of reflection characteristics and t...
This report describes a theoretical and experimental investigation of the properties of attached and...
Flat plate experiments investigating flow development downstream of normal shock wave–laminar bounda...
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in...
An investigation of the two-dimensional flow along flat plates having rounded leading edges has prov...
An experimental investigation of separated boundary-layer flow was conducted on a two-dimensional fl...
Shock-wave equations have been evaluated for a range of Mach number in front of the shock from 1.05 ...
This report discusses in detail the results obtained with devices for preventing the separation of t...
This work presents an assessment of the experimental data on separated flow in shock wave turbulent ...
A two-dimensional experimental and theoretical investigation has been conducted on an NACA 651-213 a...
This article presents an investigation on a correlation relevant to flow separation during shock wav...
The experimental study of the effect of weak shock waves on the supersonic boundary layer of the fla...
A dimensional study and an experimental investigation have been made on the pressure rise across sho...
The present status of available information relative to the prediction of shock-induced boundary-lay...
A change in flow pattern that was observed as the free-stream Mach number was increased in the vicin...
Measurements are presented at Mach numbers from about 1.3 to 1.5 of reflection characteristics and t...
This report describes a theoretical and experimental investigation of the properties of attached and...
Flat plate experiments investigating flow development downstream of normal shock wave–laminar bounda...
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in...
An investigation of the two-dimensional flow along flat plates having rounded leading edges has prov...
An experimental investigation of separated boundary-layer flow was conducted on a two-dimensional fl...
Shock-wave equations have been evaluated for a range of Mach number in front of the shock from 1.05 ...
This report discusses in detail the results obtained with devices for preventing the separation of t...
This work presents an assessment of the experimental data on separated flow in shock wave turbulent ...
A two-dimensional experimental and theoretical investigation has been conducted on an NACA 651-213 a...
This article presents an investigation on a correlation relevant to flow separation during shock wav...
The experimental study of the effect of weak shock waves on the supersonic boundary layer of the fla...