斜め衝撃波と境界層の三次元干渉場に及ぼす抽気の影響

概要

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As fundamental research on a supersonic air intake, the strong interaction between a swept shock wave induced by a 15°wedge and the turbulent boundary layer on a flat plate was experimentally studied. The effects of boundary layer bleed on the interaction are discussed. The tests were conducted under the conditions of free stream Mach number of 2.63 and 3.25 using a 1m×1m supersonic wind tunnel at National Aerospace Laboratory. Pitot pressure was measured by a rake-type Pitot probe and the vortex structure was visualized by a vapor screen technique. The direction of surface shear stress is observed by an oil film method. The bleed suppresses the size of the separation vortex induced by the swept shock. No change in the location of the vortex center is observed between the conditions with and without the bleed.
社団法人日本機械学会の論文
1994-10-25