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

概要

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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 ReL based on the model plate length was from 1.1 to 3.2 × 105, the attack angle of the model was zero, and the ramp deflection angle θw was varied from 10 to 30deg in increments of 2. The effects of ReL and θw 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 ReL-1/8Δθw, where Δθw 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. ReL-1/8 Δθw where the deviation from the model occurs and flow unsteadiness appears is found to become small with increasing ReL.
2007-11-05