吸い込みのあるくさびを過ぎる衝撃波の遷移に関する研究

概要

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An experimental and numerical study was made of shock wave transition over perforated wedges. Experiments were conducted on a shock tube equipped with double exposure holographic interferometry. Shock Mach numbers ranged from 1.07 to 3.03 in air, and the corresponding Reynolds numbers were from 2.56 × 10^3 to 5.10 × 10^4 relative to the characteristic width of perforation of 1mm. Perforated wedge models having perforation ratios ε=0.34 and 0.4 were installed in the test section. To determine the transition angle, the wedge models were rotated to adjust the wedge angle for each run. 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 a result, it is found that for stronger shock waves and ε= 0.4, the critical transition angle was decreased about 10°. A flow visualization study clarified various wave interaction mechanisms associated with the suction from the perforation. influence of the wall suction on the critical shock transition angle The successfully explained by the shock polar analysis. The PLM numerical simulation was also conducted. The numerical result agreed very well with the experimental isopycnics.
社団法人日本機械学会の論文
1990-07-25