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针对未来近空域大升力面高超声速飞行器的稀薄流动问题,采用N-S方程结合滑移模型手段,对高超声速飞行器的简化外形进行了近空域气动特性的计算分析,研究了不同滑移模型的适用性,对比了不同模型下连续流和稀薄流方法所得结果的差异性,给出了稀薄效应对飞行器气动特性影响的定量分析结果。结果表明,本文的计算结果与文献结果一致性较好;相对于热流而言,压力对稀薄效应的敏感性较弱;在较大努森数下,除了滑移模型2以外,其它模型所得热流、压力结果都一致高于DSMC结果,使得防热设计趋于保守;滑移模型2与其它滑移模型相比具有更广泛的适应性;当大升力面梯形翼的飞行高度从50km增加至80km时,滑移方法与无滑移方法所得驻点处峰值热流的偏差量约在1.6%至14.5%之间变化。
Aiming at the thin flow problem of hypersonic vehicle with near-space hypersonic near-surface in the near future, the simplified form of hypersonic vehicle is calculated and analyzed by using NS equation and slip model. The applicability of different slip models The difference between the results obtained by the continuous flow and the lean flow method under different models is contrasted. The quantitative analysis of the effect of the lean effect on the aerodynamic characteristics of the aircraft is given. The results show that the calculated results are in good agreement with the results of the literature. The pressure is less sensitive to the levitation effect than the heat flow. Under the larger Knudsen number, in addition to the slip model 2, , The pressure results are consistently higher than the DSMC results, making the thermal design tends to be conservative; slippage model 2 has a wider adaptability than other slippage models; when the height of the trapezoidal wing flight height increased from 50km to 80km , The deviation between the peak heat flux at stagnation point obtained by the slip method and the non-slip method is about 1.6% to 14.5%.