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研究了不同飞行参数下球锥形光学头罩的高超声速绕流流场的数值模拟问题。首先,分别利用k-ε湍流模型和SA湍流模型求解N-S方程,获得了球锥形光学头罩绕流流场的模拟结果。然后,将模拟结果与风洞测试得到的实验数据进行比较分析。结果表明,在高马赫数、大迎角情况下采用k-ε湍流模型可以得到相对更准确的计算结果。最后,对流场的温度、压强、密度分布特性进行了分析,给出了球锥形头罩绕流流场的压强、温度和密度随飞行参数的变化规律。
The numerical simulation of hypersonic flow field around spherical conical optical hood with different flight parameters is studied. First, the N-S equation was solved by using k-ε turbulence model and SA turbulence model respectively. The simulation results of the flow field around the spherical conical optical hood were obtained. Then, the simulation results are compared with the experimental data obtained from the wind tunnel test. The results show that the k-ε turbulence model can be used to obtain relatively accurate results at high Mach number and high angle of attack. Finally, the temperature field, pressure field and density distribution of the flow field are analyzed. The variation law of the pressure, temperature and density of the flow field around the ball cone head cover with the flight parameters is given.