摘要
本文通过风洞试验和水洞试验研究了７５°／４５°双三角翼的外翼前缘形状对大迎角分离流动的影响。试验表明，在涡破裂沿翼面向前发展的迎角范围内，外翼前缘钝化对涡态的发展、压强分布和气动力有较大影响。
The vortex visualization and surface pressure distribution for a 75°/45°double-delta wing were carried out in the water tunnel and in the low speed wind tunnel of BUAA. The inboard wing of models is sharp-edge and the outboard wing has both sharp and round leading-edge. The effect of outboard leading-edge bluntness of double-delta wing on separated flow characteristics at large incidence were studied. Experi-mental results indicate that outboard leading-edge bluntness has effect on vortex patterns development,pressure distribution and aerodynamical force at incidences range for vortex bursting.
出处
《空气动力学学报》
CSCD
北大核心
1994年第3期301-306,共6页
Acta Aerodynamica Sinica
关键词
分离流动
双三角翼
大迎角
飞机
separated flow,double-delta wing,high angle of attack,experiment study.
