極超音速流中のランプ誘起衝撃波/遷移境界層干渉の実験的研究 An Experimental Study on a Ramp-Induced Shock-Wave/Transitional-Boundary-Layer Interaction in Hypersonic Flow
An experimental investigation of a shock-wave/transitional-boundary-layer interaction was conducted on a flat plate with an aft-mounted ramp in a hypersonic gun tunnel. Test Mach number was 10, the Reynolds number range Re<SUB>L</SUB> based on the model plate length was from 1.1 to 3.2 × 10<SUP>5</SUP>, the attack angle of the model was zero, and the ramp deflection angle θ<SUB>w</SUB> was varied from 10 to 30deg in increments of 2. The effects of Re<SUB>L</SUB> and θ<SUB>w</SUB> on the characteristics of the interaction region were investigated through both schlieren visualization and heat transfer measurement. The state of reattaching boundary layers were determined from these data. The following is obtained. A model that describes how the upstream influence of a shock-wave/boundary-layer interaction scales with the parameters of the incoming flow agrees with laminar data at small Re<SUB>L</SUB><SUP>-1/8</SUP>Δθ<SUB>w</SUB>, where Δθ<SUB>w</SUB> is the incremental angle after incipient separation. The slope of the characteristic curve of the upstream influence is dependent on the type of the interaction. Re<SUB>L</SUB><SUP>-1/8</SUP> Δθ<SUB>w</SUB> where the deviation from the model occurs and flow unsteadiness appears is found to become small with increasing Re<SUB>L</SUB>.
- 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences
日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 55(646), 541-545, 2007-11-05