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。
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/C,） 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.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2007年第4期839-844,共6页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(10472013)
航空科学基金(04A51044)
关键词
无人机
气动设计
杂交设计
翼型
unmanned aerial vehicle
aerodynamic design
hybrid design
airfoil
