一体化乘波进气道改进设计和流动特征分析

为提高一体化乘波进气道的性能，通过采用壁面马赫数反正切分布内收缩基准流场和改进密切轴对称过程中的控制型线实现了对一体化乘波进气道的改进设计。通过数值仿真分析了该构型设计与非设计状态下的性能和流动特征。结果表明:设计状态下，该构型性能优良，具有前体/进气道一体化设计的特点，压缩面切除造成压缩面边界层内存在横向流动。不同攻角来流状态下，前缘弯曲激波的形状变化较小，有助于提高进气道非设计工况下的性能。侧滑来流状态下，内压缩段的流动不均匀，该构型的性能随侧滑角的变化是非线性的，内压缩段背风侧会出现低压区，诱导出流向涡，当截面内的气流流向低压区时，内压缩段内会形成双涡结构，当气流流出低压区时，第二个涡会被耗散掉，形成单涡结构。 

Improving design and flow characteristics analysis ofan integrated wave-rider inlet

For improving the performance of an integrated wave-rider inlet, the arc tangent Mach number basal flow and enhanced osculating axisymmetric control lines were adopted in the design process. Numerical simulation was conducted at on-design and off-design conditions and flow characteristics were analyzed respectively. At the design condition, the wave-rider inlet had excellent performance and the characteristic of forebody/inlet integration, however, the cross-flow phenomena appeared in the boundary-layer of compression surface as a result of cutting off. At different angles of attack, the configurations of leading edge shock were nearly the same, helping to enhance the flow capture capability at off-design conditions. For different angles of sideslip, the regularity of the performance varying with angle of sideslip was nonlinear as a result of flows ununiformity. A low-pressure region appeared at the leeward side of inner compression part, leading to a stream wise vortex. As the gas flowed to the low-pressure region on different slices, a dual-vortex structure was formed at the inner compression part. As the gas flowed out of low-pressure region, the second vortex was dissipated.