Abstract
An experimental and numerical study was made of shock wave transition over slitted wedges. Experiments were conducted in a shock tube by using double exposure holographic interferometry. Shock Mach numbers ranged from 1.07 to 3.03 in air. Slitted wedge models having perforation ratios of 0.34 and 0.4 were installed in the test section. The critical transition angle was obtained analytically by the shock polar analysis where effects of boundary conditions, wall suction, and surface roughness were empirically taken into account. As the results, it was found that for stronger shock waves and a perforation ratio of 0.4, the critical transition angle was decreased by about 10° in comparison to the detachment criterion. A flow visualization study clarified various wave interaction mechanisms associated with the wall suction. The critical transition angle was successfully explained by the shock polar analysis. The PLM numerical simulation was also conducted. The numerical result agreed very well with the experimental findings.
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Abbreviations
- M :
-
Mach number
- P :
-
pressure (P ij = Pi/Pj)
- U :
-
particle velocity
- γ:
-
specific heat ratio
- θ:
-
flow deflection angle
- φ0 :
-
angle between the incident shock wave and the wedge
- δ:
-
stream line deflection angle due to wall suction
- θθ w :
-
wedge angle
- i,j :
-
flow region, defined in Fig. 1 and 3
- s :
-
incident
- m :
-
maximum value
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Onodera, H., Takayama, K. Interaction of a plane shock wave with slitted wedges. Experiments in Fluids 10, 109–115 (1990). https://doi.org/10.1007/BF00215018
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DOI: https://doi.org/10.1007/BF00215018