希薄領域における極超音速非平衡流中の衝撃波と境界層の干渉 : 第5報,平板上の流れ場における回転温度の非平衡(流体工学,流体機械)

概要

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An experimental study of the interaction between shock wave and boundary layer over a flat plate with a sharp leading edge in hypersonic rarefied gas flow is presented. Experiments in a low density wind tunnel using an electron beam probe were conducted at the Shock Wave Laboratory, RWTH Aachen, Germany. Rotational temperatures for stagnation temperatures of T_0=670〜1000K and Kn=0.024〜0.028 based on a reference length of 0.05m were calculated by Muntz's method and by Robben and Talbot's method. The domain of quasi two-dimensional flow over the plate was determined from three-dimensional rotational temperature measurements. Nonequilibrium between translational and rotational temperatures was observed near the leading edge, and the experimental rotational relaxation length explains the rotational collision number of 2〜4.
社団法人日本機械学会の論文
2005-02-25