边条翼布局主要参数对其双垂尾抖振响应影响的风洞实验研究  

Wind-Tunnel Investigation of Twin-Vertical Tail Buffeting of Strake-Wing Configuration

作　　者：杨青[1] 李劲杰[1] 杨永年[1] 牟让科[2] 张积亭[2] 齐丕骞[2] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,陕西西安710072 [2]中国飞机强度研究所,陕西西安710065

出　　处：《西北工业大学学报》2006年第3期281-285,共5页Journal of Northwestern Polytechnical University

摘　　要：对边条翼布局的双垂尾抖振问题进行了较为深入的风洞实验研究。实验采用简化边条翼双垂尾半模。通过对垂尾的表面脉动压力、根部弯矩和翼尖加速度的测量,研究了边条后掠角、机翼后掠角、垂尾弦向位置及垂尾展向位置对边条翼布局的双垂尾抖振响应影响的规律。结果表明:①边条后掠角越大,双垂尾抖振起始迎角越大;②机翼后掠角对垂尾靠内时的抖振响应影响较小,而当垂尾靠外时,大后掠机翼的垂尾抖振响应相对较小;③垂尾弦向位置对垂尾抖振起始迎角影响较小,但对最大抖振响应影响较大;④垂尾的展向位置越靠外,垂尾抖振起始迎角就越小,但最大抖振响应也越小。Tail buffeting of twin-vertical-tail fighter has drawn much attention. An intensive wind- tunnel investigation of twin-vertical tail buffeting of strake-wing configuration was conducted in the NF-3 Wind Tunnel at Northwestern Polytechnical University. 72 configurations were tested： three sweep angles （70°, 78° and 83°） for leading-edge extension （LEX）; three sweep angles （26°, 37° and 48°） for wing; two chord-wise locations and four span-wise locations for vertical tail. The range of angle-of-attack was about 10 to 40 degrees and the wind speed was 50 meters per second. We measured： （1） the root mean square （RMS） value of root bending moment of vertical tail; （2） unsteady pressures on vertical tail; （3） tip accelerations at both leading edge and trailing edge of vertical tail. Results show preliminarily that： （1） the influence of LEX sweep angle on the vertical tail buffeting response is very large; the vertical tail buffeting onset angle of lower sweep-angle LEX is lower than that of higher sweep-angle LEX; （2） the influence of the wing sweep angle on the vertical tail buffeting response is small for the inboard tail location but large for the outboard tail location; for the outboard tail location, the vertical tail buffeting response of higher sweep-angle wing is smaller than that of lower sweep-angle wing; （3） the chord-wise location of the vertical tail has little influence on the buffeting onset angle but large influence on the maximum buffeting response intensity; （4） the span-wise location of vertical tail has large influence on the vertical tail buffeting response; the vertical tail buffeting onset angle for the outboard tail location is lower than that for the inboard tail location; the vertical tail maximum buffeting response for the outboard tail location is lower than that for the inboard tail location.

关 键 词：双垂尾抖振 边条翼布局 根部弯矩 翼尖加速度 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]