高超声速可变形双翼气动特性

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。

Aerodynamic characteristics of hypersonic morphing biplane

To study the aerodynamic performance of the morphing biplane under different angles of attack and different Mach numbers,as well as the difficulty in selecting the deflection angle of rudder with given angle of attack and Mach number,this paper combines dichotomy,genetic algorithm and Gauss-Newton algorithm to determine the deflection angle of rudder of the morphing biplane under different angles of attack and different Mach numbers.The aerodynamic characteristics of the morphing biplane and the influence of the deflection angle of rudder on the aerodynamic characteristics are analyzed.It is shown that as the Mach number is 5,and the angle of attack ranges from 1 ° to 8°,the lift-drag ratio of the morphing biplane is obviously greater (up to 4.2 times) than that of Busemann biplane.When the angle of attack is 3°,and the Mach number ranges from 0.5 to 5,the lift-drag ratio of the morphing biplane can be up to 3.4 times than that of Busemann biplane.These results indicate that the morphing biplane can maintain a high lift-drag ratio at large angle of attack and high speed range,and has better applicability and prospects in hypersonic flight.