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以定楔角乘波体设计方法为基础,研究了影响高超/超声速乘波体“乘波”的主要因素,给出了前体前缘实际气流压缩角的确定方法及影响因素,可知在相同的来流马赫数和压缩角δ下,随着前缘角θ和气流与前缘夹角α的增加,实际气流偏转角γ减小。据此,基于幂函数进气道前体构形,给出了前缘激波不脱体的限制条件及具体的判定方法,分析了乘波体典型几何特征参数对前缘激波不脱体的影响规律,结果显示在相同的来流马赫数和压缩角度下,增大前缘形状因子n,减小前体的长宽比L/W及增大前缘角均有利于激波不脱体。根据给出的前体几何参数对前缘激波脱体的影响规律曲线,对一种“前体几何外形构造+前缘激波附体条件限制”的正向前体乘波器工程设计方法进行了研究,给出了具体设计流程,并进行了初步的数值仿真验证,表明通过该方法设计的乘波前体流动特征与预期的结果吻合,说明文中所给出的激波附体条件及影响规律是可信的,乘波前体设计方法是可行的。
Based on the design method of wedge angle wakes, the main factors influencing hypersonic / supersonic wave multiplier and the “multiplied wave” are studied. The method of determining the actual airflow front angle and the influencing factors are given. At the same Mach Mach number and compression angle δ, the actual airflow deflection angle γ decreases with the increase of the leading edge angle θ and the angle between the airflow and the leading edge. Based on this, based on the power function inlet geometry, the restriction condition and specific decision method of the leading edge shock separation are given. The analysis of the typical geometry parameters of the multiplication body does not take off the front shock The results show that increasing the leading edge shape factor n, decreasing the aspect ratio L / W of the precursor and increasing the leading edge angle are conducive to the shock wave at the same Mach Mach number and compression angle body. According to the influence law of the geometric parameters of the precursor on the frontal shock off-body, a forward precursor multiplier project of “precursor geometry configuration + frontal shock attachment conditionality” Design method is given, the specific design flow is given, and the preliminary numerical simulation is carried out. It is shown that the flow characteristics of the multiplicative wave precursors designed by this method agree well with the expected results, Conditions and the impact of the law is credible, by the wavefront design method is feasible.