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4報,希薄風洞用ノズルの設計(流体工学,流体機械)

概要

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A procedure of a nozzle design for a low density wind tunnel is presented. Numerical method to estimate the flow in the nozzle is governed by the Navier-Stokes equations with the non-slip boundary condition. The design process has two step: first step is to optimize for the half angle at the nozzle exit, and second step is to select the nozzle expansion ratio. Selected half angle at the nozzle exit and expansion ratio are 15 degrees and 53.18, respectively. The performance of the nozzle on the experiments has Mach number of 4.8, and Kn based on 5cm of 0.024〜0.026. The core diameter at the nozzle exit is 4cm with water cooling on the nozzle wall. The numerical results for the Navier-Stokes simulations agree well with the experimental results, and the present procedure for the nozzle design was confirmed to be adequate.
社団法人日本機械学会の論文
2005-06-25