Abstract
Experimental studies of supersonic flow over several compression ramps are carried out in a Mach 3.0 wind tunnel; the upstream boundary layers include laminar flow, transitional flow, and turbulent flow. Fine flow structures are obtained via nano-tracer planar laser scattering (NPLS) technique, typical flow structures such as boundary layer, shear layer, and shock wave are visible distinctly. The angle of shock wave and the development of boundary layer are measured by time-averaged flow field, the spatiotemporal evolutions of flow field are revealed by two time-dependent NPLS images. Results indicate that when ramp angles are 25°, a typical separation occurs in laminar flow, and a certain extent separation occurs in transitional flow, while separation does not occur in turbulent flow. When ramp angles are 28°, laminar flow separates further, a typical separation occurs in transitional flow, by comparison, separation region in turbulent flow is small. Significant differences of the three types of ramp flows can be found in shock wave structure and flow separation.
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