Experimental Measurements of Hypersonic Instabilities over Ogive Cylinders at Mach 6
Technical Report,01 Sep 2018,26 Mar 2020
AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH WRIGHT-PATTERSON AFB United States
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Hypersonic boundary layer transition experiments were performed in the Air Force Research Lab AFRL Mach 6 Ludwieg tube over a meter long ogive-cylinder model with interchangeable nose tip angles and bluntnesses. Measurements of instabilities were captured via focused laser differential interferometry FLDI, surface mounted pressure sensors, and high speed Schlieren imagery at nominal unit Reynolds numbers ranging from 4.0106m to 1.4107m. This study attempts to isolate the effects of increasing tip angle and spherical bluntness on instabilities measured downstream over the cylindrical body of the model.
- Theoretical Mathematics
- Fluid Mechanics