高超声速乘波飞行器气动特性研究

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。

Hypersonic Waveriders Aerodynamic Performance Studies

Aerodynamic performance of hypersonic waveriders aircraft basing on cone-derived waveriders with the consideration of volumetric efficient and thermal protection is being studied by computational fluid dynamic (CFD) and wind tunnel experiment (WTE). Both the results from CFD and WTE proved that, waveriders with design condition Mach number 6 and attack angle 4°, at off-design conditions that Mach number vary within 5～7, attack angle vary within 4°～6°, it can maintain excellent aerodynamic performance. The lift-to-drag ratio is only a little below 4. At the same time, a simple viscous drag analysis method basing on reference temperature method is being given to cooperate using the results of CFD and WTE. It can be used to give viscous drag that can not be got from WTE directly, and it can be used to validate viscous drag of CFD, which is hard to be calculated accuracy too. Though it is very coarse, it is very useful for engineer application.