Unsteadiness of the shock wave structure in attached and separated compression ramp flows
Abstract
Wall pressure fluctuations have been measured upstream of the corner-line in several two dimensional, adiabatic, compression ramp flows. The nominal freestream Mach number was 3 and the Reynolds number, based on boundary layer thickness, was 1.4 million. The measurements show that the shockwave structure is unsteady in both separated and attached flows, resulting in a region in which the wall pressure signal is intermittent. Statistical properties of this intermittent region, and of the separated flow, are presented and correlated with results from other studies.
- Publication:
-
Experiments in Fluids
- Pub Date:
- January 1985
- DOI:
- 10.1007/BF00285267
- Bibcode:
- 1985ExFl....3...24D
- Keywords:
-
- Pressure Oscillations;
- Separated Flow;
- Shock Wave Propagation;
- Wall Pressure;
- Power Spectra;
- Pressure Measurement;
- Reynolds Number;
- Two Dimensional Flow;
- Wind Tunnel Tests;
- Fluid Mechanics and Heat Transfer