Study on the Performance Characteristics of Osculating Cone Waverider According to Shock Wave Angle

초록

The design of hypersonic vehicles emphasizes superior aerodynamic performance. In this study, we investigate the effects of varying shock wave angles on the aerodynamic performance of an osculating cone waverider under both on- and off-design conditions. Three configurations were designed under identical conditions with respective shock wave angles of 14 degrees, 15.5 degrees, and 17 degrees. After applying boundary layer correction, computational fluid dynamics (CFD) analyses were conducted to obtain and compare the aerodynamic characteristics at the on-design point and under various off-design conditions. The results show that configurations with smaller angles exhibited superior performance in terms of lift-to-drag ratio at the on-design point and under sideslip conditions. Conversely, configurations with larger angles showed lower lift-to-drag ratios at the on-design point. However, they experienced less performance degradation under off-design conditions involving variations in the angle of attack and Mach number. Thus, our results shed new light on selecting an optimal shock wave angle in the design of hypersonic osculating cone waveriders by considering both on- and off-design aerodynamic performance.

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