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根据密切锥乘波体的设计几何关系,提出双后掠乘波体概念,给出了双后掠乘波体设计的参数与生成乘波体外形之间的关系。使用非均匀有理B样条(NURBS)表达包括圆和直线的激波出口型线辅助设计,研究了钝头区域可控、后掠区域可控的乘波体外形设计方法。使用CFD数值计算方法验证了设计方法的有效性,同时研究了双后掠乘波体外形的性能优势,结果表明在保持高超声速高性能的基础上适当设计外形在低速状态、纵向稳定性和涡效应增升方面具有性能优势,为大空域宽速域高超声速飞行器的研制开拓了新的途径。
According to the geometrical relationship of the closely conic multiplier, the concept of double-swept multiplier is proposed, and the relationship between the parameters of dual-swept multiplier and the shape of multiplicator is obtained. The non-uniform rational B-spline (NURBS) expression is used to design a shock-exit line design including circular and straight lines. The CFD numerical calculation method is used to verify the effectiveness of the design method. Meanwhile, the performance advantage of the double-swept wave form is studied. The results show that the shape of the double-swept wave-front body can be properly designed with the hypersonic performance at low speed, It has the performance advantage in the aspect of increasing the effect and opens up new avenues for the research and development of the large space hypersonic vehicle with large speed.