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描述了基于密切曲锥的乘波构型一体化飞行器设计方法。其特点是采用曲面乘波压缩前体,前体进气道压缩面基准流场由激波和等熵压缩波轴对称流场组成,三维乘波面采用密切曲锥方法由前缘线各点流线跟踪拟合构成流面;前体上表面由变半径轴对称特征线法生成基准流场并流线跟踪构成流面;尾喷管根据发动机燃烧室出口参数构造特征线流场并流线跟踪得到膨胀型面。快速的分析工具采用工程计算、一维燃烧室计算与经验公式相结合的方法对飞行器性能进行初步评估。所设计的三米量级一体化模型飞行器通过数值计算和风洞试验对性能进行了验证,结果表明,飞行器在设计状态基本达到设计要求,发动机正常点火工作,飞行器得到正推力,采用的气动性能快速分析估算方法对气动力的预测较为准确。
The design method of integrated multi-wave structure aircraft based on close curved cone is described. Its characteristic is that the surface compressional precursor is used to compress the precursors, and the baseline flow field of the inlet compression surface of the precursor is composed of shock wave and isentropic compression wave axis symmetrical flow field. The line flow is simulated by the line-tracking fitting. The reference flow field is generated by the variable-radius axisymmetric characteristic line method on the upper surface of the precursor, and the flow line is traced to form the flow surface. The tail-flow line is constructed according to the outlet parameters of the combustion chamber of the engine. Get the expansion type surface. The rapid analysis tool uses engineering calculation, one-dimensional combustion chamber calculation and empirical formula to carry out a preliminary assessment of aircraft performance. The three-meter-scale integrated model aircraft has been verified by numerical calculation and wind tunnel test. The results show that the design of the aircraft basically meets the design requirements, the engine normally ignites, the aircraft is thrust, and the aerodynamic performance The method of rapid analysis and estimation of aerodynamic force is more accurate.