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用计算流体力学和风洞试验的方法对以锥导乘波体为基础生成的高超声速乘波飞行器的气动性能进行了研究。结果表明,以马赫数6,攻角4度为设计状态的乘波体,在马赫数5~7,攻角4~6度的范围内,都具有良好的气动特性,升阻比接近4。最后,提出了一个简单的以参考温度方法为基础的粘性阻力分析方法。该方法配合使用风洞试验和计算流体的结果,可以用来验证计算流体中难以计算准确的粘性阻力,也可以用来分析在风洞试验难以直接得到的粘性阻力。对于工程上的粘性阻力分析是一个有用的办法。
The aerodynamic performance of Hypersonic wave-based aircraft based on the cone-guided wave multiplying body was studied by computational fluid dynamics and wind tunnel test. The results show that the multiplication body designed with Mach number 6 and attack angle 4 has good aerodynamic characteristics with Mach number of 5 ~ 7 and angle of attack of 4 ~ 6 degrees, and the drag - resistance ratio approaches 4. Finally, a simple viscous resistance analysis method based on the reference temperature method is proposed. This method, combined with the wind tunnel test and the fluid calculation, can be used to verify that it is difficult to calculate the exact viscous drag in the computational fluid and to analyze the viscous drag that is not readily available in wind tunnel tests. For engineering viscous resistance analysis is a useful way.