粘性干扰效应是飞行器在高空、高马赫数飞行状态下所面临的诸多重要物理效应之一,对飞行器在这一区段飞行时的气动性能有着极其重要的影响。本文基于粘性干扰理论,结合参考温度方法提出了一种能够考虑粘性干扰效应的高超声速乘波体气动性能的工程预测方法,克服了传统工程预测方法不能计及粘性干扰效应的不足。文中对该方法的合理性进行了理论分析,并在飞行高度30～70km,飞行马赫数15～20范围内,通过本文提出的方法与传统工程方法以及计算流体力学(CFD)方法计算结果的比较,验证了本文所提出的方法的有效性。 Viscous interference effect is one of the most important physical effects that an aircraft encounters at high altitude and high Mach number. It has an extremely important influence on the aerodynamic performance of an aircraft during its flight. Based on viscous interference theory and combined with reference temperature method, an engineering prediction method of aerodynamic performance of hypersonic multiplied wave body considering viscous interference effect is proposed, which overcomes the shortcomings of traditional engineering prediction methods that can not account for the viscous interference effect. In this paper, the rationality of the method is theoretically analyzed and compared with the traditional engineering method and computational fluid dynamics (CFD) method in the range of flight altitude of 30 ~ 70km and flight Mach number of 15 ~ 20 , Verify the effectiveness of the proposed method.