吸气式飞行器进气道唇口三维激波/激波干扰

对吸气式飞行器进气道唇口处三维曲面激波/弓形激波干扰流场进行数值模拟,利用典型三维气动干扰试验对采用的数值计算方法进行验证。利用拼接网格技术及逆距离加权插值方法获得入口处流场的非守恒变量,作为激波干扰研究的入口边界条件。数值模拟表明,唇口处激波干扰流动的三维效应十分显著,曲面激波与弓形激波产生斜交,尽管唇口前缘半径很小,但Edney提出的6类激波干扰类型可能沿唇口展向方向同时存在；第Ⅲ和Ⅳ类激波/激波干扰的诱导使得唇口热流分布异常严酷；激波相交处形成斜向“伤疤”状局部高热流条带,峰值热流达到参考热流的4~6倍,可能引起唇口结构的局部烧蚀或破坏。 

Three-dimensional shock/shock interaction of airbreathing vehicle’s inlet lip

Numerical simulation on three-dimensional interaction between curved oblique shock wave and bow shock wave was studied under the condition of small radius of the cylinder. The numerical method validation was carried out by using the typical three-dimensional aerodynamic interference model. The entrance boundary condition of inlet was obtained by the application of patched grid technology and inverse-distance interpolation method. It indicated that three-dimensional feature of the interactions was strong as the curved oblique shock and bow shock intersected at small angle and six types of shock-shock interactions proposed by Edney may exist over the lip along the lateral direction, although the radius of cowl lip was small. Thermal environment induced by the type Ⅲ and type Ⅳ shock-shock interactions was severe. And the shape of the high heat flux region was like a “scar” on the cowl lip. Heat flux of the scar was 4 to 6 times of the reference heat flux under the same flow condition. This may lead to the ablation or structure damage of the cowl lip.