三角翼大攻角分离流开缝吸气效应研究  

INVESTIGATION OF EFFECT OF SUCTION ON DELTA WING SEPARATION FLOW AT HIGH ANGLE OF ATTACK

作　　者：白鹏[1] 周伟江[1] 汪翼云[1] 

机构地区：[1]北京空气动力研究所,北京100074

出　　处：《航空学报》1999年第5期393-398,共6页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金

摘　　要：分别采用数值方法和实验方法研究了大后掠角三角翼大攻角条件下，背风面开缝吸气对流场结构和气动力特性所造成的影响。数值模拟采用 Ｈａｒｔｅｎ Ｙｅｅ 的二阶精度隐式 Ｔ Ｖ Ｄ 格式和 Ｎ Ｓ方程；实验采用激光蒸汽屏流场显示和应变天平测力技术。通过在三角翼背风面开缝吸气，抽掉低能气流，实现增升的效果不理想，同二维吸气涡控制增升效果相差很远，这主要是由于二维同三维分离产生机理上的差异所造成的。The numerical method and experiment technique were conducted to investigate what effect will be produced on the flow structure and aerodynamics over the highly swept delta wing with suction technique in the Lee Side at high angle of attack . Harten Yee's second order TVD scheme and Navier Stokes equations were utilized in numerical simulation. A laser illumination for flow visualization and the strain gauge balance were carried out in experiment. The main result was that through suction in the delta wing Lee Side to reel off the low energy flow, the effect of increasing lift was not satisfied and much more lower than the effect of the two dimensional condition. The reason is the basic difference between the three dimensional separation and the two dimensional separation.

关 键 词：大攻角 三角翼 分离流 涡控制 开缝吸气效应 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]