超音速ノズル内の衝撃波による乱流境界層のはく離

概要

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Experiments on the shock wave/turbulent boundary layer interaction were conducted at the free stream Mach number M_<1e> of 1.97 to 2.50 and the Reynolds number based on the boundary layer thickness Re_<δ1> of 3.1×10^4 to 5.8×10^4 using a supersonic nozzle having a divergent half angle of 10 degrees. Nozzle wall static pressure measurements and the schlieren optical observation of the interaction region were carried out. Also, the effects of M_<1e> and Re_<δ1> on the shock-induced turbulent boundary layer separation were investigated theoretically. As a result, the analytical results of the ratio p_s/p_1 of the separation pressure p_s to the pressure at the onset of the interaction p_1 were found to increase with increasing M_<1e> for a fixed Re_<δ1> and to increase with increasing Re_<δ1> for a fixed M_<1e> and to provide excellent agreement with the experimental results on the shock-induced turbulent boundary layer separation.
一般社団法人日本機械学会の論文
1997-03-25