摘要
通过对融合体型机身进行表面测压和PIV(Particle Image Velocimetry)流动显示实验,研究了大攻角下鸭翼/边条对机身气动特性的影响规律.结果表明:加装鸭翼后攻角小于50°时机头区流动变化不大,超过50°攻角后,机头区法向力显著下降,并且随着攻角增加受影响区域向头部方向扩大;加装鸭翼致使鸭翼区截面法向力大幅增加.加装边条改善了边条区流动,边条涡对机头涡产生有利诱导,增大了边条区法向力.加装边条/鸭翼时,对机头区及鸭翼区流场的影响由鸭翼起主控作用,对边条区流场的影响由边条起主控作用.
The influence of canard wing and strake on aerodynamic characteristic of chined forebody was studied by surface pressure measurement and particle image velocimetry（PIV） flow measuring systematically.It shows that there is only a little effect of canard wing on the flowfield around nose area under 50° angle of attack（AOA）.If angles of attack are larger than 50°,the normal forces on nose region decrease sharply and influenced region by canard wing is enlarged toward the nose region with increasing AOA.The normal force in the canard wing region is increased sharply by setting canard wing.The flowfield on the strake region is improved and the normal force on the strake region is increased by setting the strake.If the canard wing and strake are set simultaneously,the flow behaviors in nose and canard regions will be dominated by canard wing and one in strake region will be dominated by strake.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2010年第5期596-600,共5页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家自然科学基金重点基金资助项目(10432020)
国家自然科学基金资助项目(10872019)
国家自然科学基金青年基金资助项目(10702004)
关键词
融合体型机身
大攻角
气动特性
chined forebody
high angle of attack
aerodynamic characteristic
