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为了提高大迎角下三角翼的机动性,在北航0.6m×0.6m×4.0m水槽中对后掠角Λ为70°的三角翼模型进行流动显示实验来研究尖顶襟翼对三角翼前缘涡破裂的影响。迎角α范围为30°～50°,弯折位置为30%c,向下弯折角B为0°～30°。试验结果表明:低头的尖顶襟翼对延迟三角翼前缘涡的破裂有显著效果,且弯折位置在涡破裂点附近时,推迟涡破裂的效果较好。迎角α≤40°时,存在一个推迟前缘涡破裂最有效的弯折角度。对于迎角α=40°,当弯折角度B=20°时效果最佳,可使前缘涡涡破裂点位置推迟33%～35%c。
In order to improve the flexibility of the delta wing at high angle of attack, a flow experiment on a delta wing model with a sweep angle Λ of 70 ° was performed in a 0.6m × 0.6m × 4.0m Beihang waterway to study the effect of the apex flap on the delta wing front The effect of vortex rupture. Angle of attack α range of 30 ° ~ 50 °, the bending position of 30% c, downward bending angle B 0 ° ~ 30 °. The experimental results show that the bowed flaps have a significant effect on the rupture of the leading edge vortex of the delayed delta wing. When the bending position is near the rupture point of the vortex, the vortex rupture is delayed. When the angle of attack α ≤ 40 °, there is a most effective bending angle to delay the front vortex rupture. For the angle of attack α = 40 °, the best effect when the bending angle B = 20 ° can delay the position of the leading edge vortex rupture by 33% -35% c.