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为了研究乘波体几何外形参数和飞行参数对前体/进气道一体化设计的影响,采用理论分析和数值模拟相结合的方法,以马赫数Ma=6和攻角α=0为设计状态、进气道总压恢复系数和前体阻力系数为目标函数,对乘波体前体/进气道进行了优化设计,并在此基础上研究了攻角、马赫数、前缘半径、前体宽度对气动参数的影响。结果表明:该乘波体前体/进气道构型具有良好的攻角特性,总压恢复系数比基准构型提高17.79%,阻力系数比基准构型降低78.5%,符合高超声速飞行器高升力、低阻力的要求,且非常适合小攻角高超声速巡航飞行;为了得到较高升阻比的前体,在前缘半径R≤2mm的范围内进行流场反设计时,可以将设计马赫数的取值比预期低一些。
In order to study the influence of the geometric shape parameters and the flight parameters of the wave body on the integrated design of the precursor / air intake, a combination of theoretical analysis and numerical simulation is used to design the Mach number Ma = 6 and the angle of attack α = 0 , Total inlet pressure recovery factor and precursor drag coefficient as objective function, the precursor / inlet of multiplier body is optimized. Based on this, the effects of angle of attack, Mach number, leading edge radius, front Influence of body width on aerodynamic parameters. The results show that the precursor / inlet configuration has good angle-of-attack characteristics, the total pressure recovery coefficient is 17.79% higher than the baseline configuration and the drag coefficient is 78.5% lower than the baseline configuration, which is in line with the high-lift , Low resistance requirements, and is very suitable for small angle of attack hypersonic cruise flight; In order to get a higher lift-drag ratio of the precursor, the front edge radius R ≤ 2mm range of flow field design, you can design Mach number Value is lower than expected.