短舱扰流片对螺旋桨飞机的失速减缓研究  

Research on stall deceleration for nacelle strake design of engine propeller aircraft

作　　者：温庆 杨康智 魏猛 程志航 贾重任 WEN Qing;YANG Kangzhi;WEI Meng;CHENG Zhihang;JIA Zhongren(Entire Department,General Huanan Aircraft Industry Company,Limited,Aviation Industry Corporation of China,Limited,Zhuhai Guangdong 519040,China)

机构地区：[1]中航通飞华南飞机工业有限公司总体部,广东珠海519040

出　　处：《航空动力学报》2023年第11期2610-2617,共8页Journal of Aerospace Power

摘　　要：翼吊螺旋桨发动机的短舱对飞机的升力失速特性有明显的影响,采用数值模拟方法研究了短舱扰流片对失速的影响效果。数值仿真和风洞试验表明,在零推力状态,某大型四发螺旋桨飞机在超过失速迎角以后,内外发动机之间的机翼首先分离,并快速推进到机翼前缘,失速以后升力损失达到最大升力系数的30%左右。为了限制机翼的分离速度,在外发短舱的内侧,安装了一个扰流片。仿真结果表明,在最佳设计位置,明显改善了失速特性,与无扰流片状态相比失速以后升力损失减小50%左右,失速迎角没有明显变化。不同的扰流片安装位置对失速的改善效果差异明显,从最佳位置向周向以及螺旋桨方向移动会造成扰流片失效,向机翼方向移动对改善机翼分离速度有效,但是会明显降低失速迎角,向机翼方向移动后,受周向位置的影响减小。针对最佳设计位置开展了着陆构型零推力状态的风洞试验验证,加装扰流片以后,机翼失速后的升力损失由0.92降低至0.42左右,升力损失减少54%,与数值仿真结论基本一致。The effect of nacelle strake on stall was studied by numerical simulation.Numerical simulation and wind tunnel test showed that in the state of zero thrust,after a large four engine propeller aircraft exceeded the stall angle of attack,the wings between the internal and external engines first separated and quickly advanced to the leading edge of the wing,and the lift loss reached about 30%.In order to limit the separation speed of the wing,a nacelle strake was installed inside the outboard engine nacelle.The simulation results showed that the stall characteristics were significantly improved at the optimal design position,the lift loss after stall was reduced by about 50%compared with the state without nacelle strake,and the stall angle of attack did not change significantly.Different installation positions of nacelle strakes had obvious differences in improving stall;movement from the best position to the circumferential direction and propeller direction caused the failure of nacelle strake.Movement to the wing direction wa effective to improve the wing separation speed,but it significantly reduced the stall angle of attack.After moving to the wing direction,the influence of circumferential position was reduced.A wind tunnel test was carried out to verify the landing configuration in zero-thrust condition according to the optimal design position.After adding the nacelle strake,the lift loss of the airfoil after stall was reduced from 0.92 to about 0.42,and the lift loss was reduced by 54%,which was basically consistent with the numerical simulation conclusion.

关 键 词：螺旋桨 短舱 扰流片 安装位置 失速 升力损失 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]