【摘要】 发展了用于高性能无人机翼型设计的杂交优化设计方法。针对“类全球鹰”翼型的算例表明,该方法能满足低速时高升力(CL)和跨声速巡航时高气动效率(CL/CD)两方面要求。优化翼型较初始翼型,其低速时的设计升力系数提高了19.80%,跨声速巡航时的设计升阻比提高了37.45%,并且在较大的速度区间内优化翼型都具有良好的综合性能。杂交优化设计方法可为高空长航时无人机的设计提供参考。更多还原

【Abstract】 A hybrid optimization method was developed for the design of high performance unmanned aerial vehicle(UAV)airfoil.Computation case of “quasi-global hawk” airfoil showed that this method could satisfy the demands of high lift coefficience(CL)on low speed condition and high aerodynamic efficiency(CL/CD)on transonic cruise speed condition.Comparing with the original one,the optimal airfoil’s design CL on low speed condition was arised by 19.80% and on transonic cruise speed condition design CL/CD was arised by 37.45%,and the optimal one also had better intergal performance in a wide speed range.The hybrid optimization method could be valuable for the design of high altitude long endurance UAV.更多还原