衝撃風洞貯気槽温度に対する衝撃波/境界層干渉の影響

概要

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Numerical prediction of the reservoir temperature in a shock tunnel is performed by simulating the unsteady flow field in the driven tube and nozzle of the shock tunnel of Nagoya University. The axisymmetric, compressible Navier-Stokes equations are numerically solved by a finite volume code with the third order MUSCL in space and the fourth order Runge-Kutta method in time. The results show that the flow pattern near the end of the driven tube is highly complicated, because the reflected shock wave interacts with the boundary layer and contact discontinuity. The present simulation estimates the reservoir temperature of the shock tunnel at a maximum value of 876K, which agrees with the value predicted from the heat flux experimentally measured at a model in the test section.
社団法人日本航空宇宙学会の論文
2005-01-05