尖顶襟翼对70°三角翼气动力影响的实验研究  

Experimental studies on the aerodynamic characteristics of a 70-degree delta wing with apex flap

作　　者：王晋军[1] 徐燕[1] 李亚臣[1] 

机构地区：[1]北京航空航天大学流体力学研究所,北京100083

出　　处：《空气动力学学报》2002年第1期109-114,共6页Acta Aerodynamica Sinica

基　　金：国防科技预先研究基金资助项目 (项目编号 0 0J13.1.3HK0 12 4 )

摘　　要：在水洞实验的基础上 ,进一步通过风洞实验研究了尖顶襟翼对 70°三角翼气动特性的影响。实验迎角为 2 0°～ 50°,弯折位置为 30 %c,向下弯折角B为 0°～ 30°。实验结果表明 :尖顶襟翼向下弯折可以推后失速迎角约 5°;在失速迎角后 ,尖顶襟翼对升力系数的提高有明显的效果 ,而对阻力系数的影响不大 ;另外 ,低头的尖顶襟翼可以减弱三角翼的滚转力矩。Based on the water tunnel experimental results, the aerodynamic characteristics of a 70 degree delta wing with apex flap were investigated in the wind tunnel. The range of attack angles varied from 20° to 50°, and the apex flap was hinged at 30% root chord station with the flap angles of 0°～30°.The dropping apex flap was found to take advantage of the augment of 5 degree in the stalling angle. The apex flap deployment had a promising effect on the lift after stalling angle, but it had little effect on the drag. Moreover,the flap was successful in improving the roll moment.

关 键 词：尖顶襟翼 三角翼 大迎角 分离流 气动特性 

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]