RESEARCH ON DESIGN METHOD OF PLANFORM-CUSTOMIZED WAVERIDER FROM VARIABLE MACH NUMBER CONICAL FLOW

The traditional waverider design method has a single design state, and the the aerodynamic performance ad-vantage of high lift-drag ratio is difficult to maintain when the waverider deviates from the design point state, which limits the application of the waverider in wide-speed aerodynamic configuration design. In this paper, based on the waverider design theory of the osculating-cone treatment, by employing the conical flows with differ-ent Mach numbers in different osculating planes, the planform-customized waverider design from variable Mach num-ber flows is proposed based on the geometric design relations in the osculating-cone method, and the double swept waveriders with different spanwise Mach number distribution were generated ,which shared the same customized leading edge curve. Computational fluid dynamics techniques were employed to analyze the shock wave structure of flow field, aerodynamic forces and longitudinal stability of the waveriders. Compared with conventional waveriders using fixed conical flows, the wide-speed performances of this kind of planform-customized waverider were explored in hypersonic stage. Results showed that the planform-customized waverider design from variable Mach number flows is feasible, enlarging design space efficiently. In the wide-speed range of hypersonic stage, the waverider from varia-ble Mach number flow featured balanced lift-to-drag (L/D) ratio and volume efficiency. However, when the planform shapes were identical, the difference of aerodynamic centers between the variable-Mach-number waveriders and fixed-Mach-number waveriders was significantly slight, indicating that the variable Mach number flows as basis flows had nearly no effect on longitudinal stability. Meanwhile, compared with the fixed-Mach-number waveriders with equal volume and identical planform shape, the wide-speed L/D ratio of the variable-Mach-number waveriders were not su-perior in hypersonic stage.