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将乘波体作为以吸气式超燃冲压发动机为动力的高超声速飞行器的前体,不仅可以发挥乘波体优异的气动力性能,而且起到了高超声速飞行器前体对来流的预压缩作用.为了进一步提升乘波前体的预压缩作用,基于Sobieczky提出的吻切锥原理,发展了一种新的多级压缩乘波体外形的设计方法.将该设计方法应用到锥导和吻切锥乘波体的设计中,生成了具有多个压缩面的多级压缩锥导和吻切锥乘波体,同时对相同设计条件和具有相同投影曲线的前缘条件下获得的三级压缩锥导和吻切锥乘波体的性能进行了对比分析.研究结果表明数值模拟计算结果与设计预期完全吻合,该多级压缩乘波体设计方法可以应用于锥导和吻切锥乘波体.
Using wave body as a precursor of a hypersonic vehicle powered by an aspirated scramjet can not only exert the aerodynamic performance of the multiplier body but also precompress the flow of the hypersonic vehicle precursor In order to further enhance the precompression function of the wavefront precursors, a new design method of multi - stage compressional wave body shape is developed based on the principle of kissing cone proposed by Sobieczky.The method is applied to the cone guide and kissing In the design of the cone multiplication wave body, a multi-stage compression cone guide and kiss cut cone multiplication body with multiple compression surfaces is generated. Meanwhile, for the same design conditions and the three-stage compression cone with the same projection curve The results show that the numerical simulation results are in good agreement with the design expectation. The multi-stage compression multiplication body design method can be applied to the cone-guided and kiss-cut cone multiplication bodies.