随着当今飞行器飞行速度的提高,三维超声速内流道的设计需求日益增加。提出一种基于特征线追踪的气动反设计方法,以解决三维超声速粘性流场设计问题。为了验证特征线追踪方法的设计能力,将其应用于二维超声速喷管和三维方转圆流道设计中。结果表明,设计所得流道内部不存在集中的膨胀波和压缩波,获得了流动均匀的菱形试验区,出口处马赫数误差低于0.5%。特征线追踪方法能够直接设计超声速粘性流场,避免了传统的边界层修正技术引入的设计误差,实现了既能满足预设流场参数分布,又能保证入口和出口形状的三维异形截面超声速流道设计。 With the improvement of the flight speed of today’s aircraft, the design requirements of the three-dimensional supersonic inner flow channel are increasing. A pneumatic inverse design method based on characteristic line tracking is proposed to solve the design problem of 3D supersonic viscous flow field. In order to verify the design ability of the method of feature line tracking, this method is applied to the design of two-dimensional supersonic nozzle and three-dimensional square-turn channel. The results show that there is no concentrated expansion wave and compression wave in the designed flow channel, and a uniform diamond test area is obtained. The Mach number error at exit is less than 0.5%. The characteristic line tracking method can directly design the supersonic viscous flow field and avoids the design error introduced by the traditional boundary layer correction technology. The three-dimensional shaped cross-section supersonic flow stream that can satisfy the preset flow field parameter distribution and ensure the shape of the inlet and the outlet Road design.