飞翼布局无人机进排气效应风洞试验研究  

Wind tunnel experimental research on effect of air intake and exhaust on the aerodynamic performance of flying wing UAV

作　　者：郁新华[1] 陶于金[1] 张琳[1] 

机构地区：[1]西北工业大学无人机研究所,陕西西安710072

出　　处：《空气动力学学报》2013年第4期494-497,510,共5页Acta Aerodynamica Sinica

摘　　要：飞机进排气会对全机气动性能产生明显的影响。采用引射式动力模拟器对飞翼布局无人机开展进排气效应模拟,分析进排气对全机气动特性的影响。试验结果表明:进排气对飞翼布局升力影响不明显,对阻力影响量比较大,可使全机最大升阻比降低1～4左右,而喷流能使全机最大升阻比下降1～1.8左右,进排气效应使得全机俯仰力矩增加,但纵向静安定度基本不变;进排气对全机横航向特性影响不大,对襟翼效率影响也甚微。可作为飞翼无人机气动布局设计的参考。The effect of air intake and exhaust on the aerodynamic performance of flying wing UAV is investigated in details.Model description and experimental setup is introduced,experimental results are analysized.The longitudinal aerodynamic performance variations among different flow flux,the aerodynamic performance variations among different eject pressure ratio,the lateral and directional aerodynamic characteristics of UAV and the comparison of the aerodynamic performances of the flap with and without eject are presented.The air intake and exhaust can increase the value of drag and the value of pitching moment,the liftdrag ratio will decrease 1to 4,but the eject has little effect on the pitching moment.The S-shaped inlet has important effect on the pitching moment,the lift-drag ratio will decrease 1-1.8by eject.Finally,Air intake and exhaust have little effect on the lateral and directional aerodynamic characteristics of UAV and flap efficiency.

关 键 词：进排气 无人机 风洞试验 气动特性 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]