进口轴向和水平投影同时可控的内收缩进气道设计

为了满足两侧进气布局高超声速飞行器乘波前体与进气道一体化设计要求,基于特征线法和流线追踪技术提出了一种进口轴向投影和水平投影同时可控的内收缩进气道设计方法。采用该方法设计了进口轴向投影和水平投影均为超椭圆的内收缩进气道并在设计点(马赫数为6.0）对其进行数值仿真验证。结果表明:进气道进口轴向投影和水平投影均符合预期设计。进气道能保持基准流场的波系结构和沿程压力分布,无黏时可以全捕获来流,喉道截面性能与基准流场基本相等。有黏时,进气道也具有较高的压缩效率,流量系数和出口总压恢复系数分别为0.96和0.56。因此，上述设计方法可行有效。 

Design of inward turning inlet with simultaneous control of intake axial and horizontal projections

Based on the rotational method of characteristics and streamline tracing technique, the design method was developed for inward turning inlet with control of the axial and horizontal projections of intake, so as to meet the integrated design requirements of hypersonic vehicle waverider forebody and inlet with both sides intake layout. The inward turning inlet was designed utilizing this design method for the axial and horizontal projections of intake of super ellipse. Numerical simulation was conducted at design point Mach number of 6.0. The results indicate that the axial and horizontal projections of intake conform to the anticipated design. The inlet can retain the wave structure and pressure distribution of basic flowfield, and capture all of free incoming flow under the inviscid condition. Its performance of throat plane is almost equal to basic flowfield. Under the viscous condition, the inlet has high compression efficiency; the flow coefficient and total pressure recovery coefficient of exit plane are 0.96 and 0.56, respectively. This design method is feasible and effective.