Abstract:
Waverider generated by streamline tracing has a large viscous error in the inner flow of its inlet. To design the integrated airframe-inlet waverider with no reflected shock waves in its isolator, a method of viscous boundary-layer correction has been developed in the present study for the cone-derived or osculating-cone waverider with multistage shock waves. The new approach is based on the method of characteristics (MOC) for the waverider design of multistage forebody and truncated Busemann inlet, and couples with the integration method of von Karman momentum equations for the hypersonic compressible axisymmetric flow. The displacement thickness of boundary layer is corrected to improve the consistency with the design expectation in viscous state. Numerical simulations of two waveriders before and after the viscous correction are comparatively validated under the design conditions. Meanwhile, for given Mach numbers and angles of attack, the aerodynamic performances are analyzed off the design conditions. The results show that, in the design state, the two-stage forebody shock waves and the entrance shock wave of the viscous corrected configuration are basically consistent with the design expectation that the reflected shock waves in its isolator are eliminated. The flowrate ratio of the inlet increases by 4.51%, and the total pressure loss at the outlet decreases by 8.23%. Off the design state, aerodynamic performances of the corrected waverider show the same superiority, which has stronger incoming flow capture capability and smaller total pressure loss. The developed method can increase the accuracy for the design of integrated airframe-inlet waveriders, and can also be applied to the precise design of the forebody and inlet of air breathing hypersonic vehicles.