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日本名古屋大学的激波风洞,通过喷管和被驱动管内非定常流场模拟,完成了激波风洞中接受罐温度的数值预估。采用空间三阶精度MUSCL与时间4阶精度RungeKutta的有限体积法,求解轴对称可压缩NS方程组。计算结果表明,在靠近被驱动管末端的流动模态是很复杂的,原因是反射激波附面层和接触面间相互作用的结果。估计激波风洞的接收罐温度最大值为876K,这与试验段中实测模型热流所预估的数值相一致。
The shock wind tunnel at Nagoya University in Japan simulated the unsteady flow field inside the nozzle and the driven tube and estimated the temperature of the receiving tank in the wind tunnel. The axially symmetric and compressible Navier-Stokes equations are solved by using finite volume method of third-order space accuracy MUSCL and time-order RungeKutta. The calculated results show that the flow mode near the end of the driven tube is very complicated because of the interaction between the reflection shock and the contact surface. It is estimated that the maximum receiver tank temperature for a wind tunnel is 876K, which is consistent with the predicted value of the measured model heat flow in the test section.