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结合直升机飞行特性及旋翼工作气动环境,提出了适用于中型运输直升机旋翼翼型优化设计的目标函数及约束条件.在此基础上采用遗传算法,以“黑鹰”(UH-60A)直升机旋翼翼型SC1095为基础翼型,进行多目标、多状态以及多约束条件下的旋翼翼型优化设计.优化翼型同SC1095翼型相比弯度稍大,最大厚度略有增加.结果表明:优化翼型气动力特性在满足约束条件的情况下,零升力矩系数减小了57.2%,最大升力系数增加了3.7%,阻力系数减小了7.5%.同时,非定常动态失速状态下的气动特性也有一定的改善,阻力系数和力矩系数的发散范围均有明显的减小.此外,悬停状态计算结果表明:采用优化翼型构成的旋翼与SC1095旋翼相比,具有更高的悬停效率及更低的力矩系数.
Combining the flight characteristics of helicopter and the aerodynamic environment of rotor working, the objective function and constraint condition for rotor airfoil optimization design of mid-size transport helicopter are proposed. On the basis of this, genetic algorithm is used to design a helicopter with “Black Hawk” (UH-60A) helicopter The rotor airfoil SC1095 is a base airfoil designed for multi-objective, multi-state and multi-constrained rotor airfoil optimization.The optimized airfoil is slightly larger than the SC1095 airfoil with a slight increase in maximum thickness.The results show that the optimization The aerodynamic characteristics of airfoils satisfy the constraints, the zero-lift moment coefficient is reduced by 57.2%, the maximum lift coefficient is increased by 3.7%, and the drag coefficient is reduced by 7.5% .At the same time, the aerodynamic characteristics under unsteady dynamic stalling condition But also a certain improvement, drag coefficient and torque coefficient divergence range are significantly reduced.In addition, the hover state calculation results show that: the rotor with the optimized airfoil SC1095 rotor rotor compared with higher hover efficiency and Lower torque factor.