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为研究高超声速可变形双翼在不同迎角和不同马赫数条件下的气动特性,并针对在给定的迎角和马赫数条件下可变形双翼的舵面偏转角选取困难的问题,通过结合二分法、遗传算法和高斯牛顿算法对处于不同迎角和不同马赫数条件下的可变形双翼的舵面偏转角进行了选取确定,分析了可变形双翼的气动特性和舵面偏转角对其气动特性产生影响的机理。研究表明:当来流马赫数为5,迎角从1°~8°变化时,可变形双翼的升阻比明显大于Busemann双翼的升阻比,最大可达4.2倍;当迎角为3°,来流马赫数从0.5~5变化时,可变形双翼的升阻比最大可达Busemann双翼升阻比的3.4倍。结果表明可变形双翼在大迎角和大速度范围内均能保持高升阻比,在高超声速飞行中将具有更好的应用价值和前景。
In order to study the aerodynamic characteristics of hypersonic deformable wings at different angles of attack and different Mach numbers, and in view of the difficulty of choosing deflection angles of deformable wings under given angles of attack and Mach number, Method, genetic algorithm and Gauss Newton algorithm, the deflecting angles of deformable wings at different angles of attack and different Mach numbers were selected and determined. The aerodynamic characteristics of the deformable wings and the deflection of rudder surface were analyzed. Impact of the mechanism. The results show that when the Mach number is 5 and the angle of attack is from 1 ° to 8 °, the drag / drag ratio of the deformable wing is obviously larger than that of the Busemann wing, up to 4.2 times. When the attack angle is 3 ° , When the Mach number changes from 0.5 to 5, the maximum drag-resistance ratio of the deformable wing can reach 3.4 times that of the Busemann wing. The results show that the deformable wing maintains a high lift-drag ratio both at high angles of attack and at high speed, and will have better application value and prospect in hypersonic flight.