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对带不同前缘切口和弧面下反角以Clark-Y翼型为基础翼型的翼伞分别进行了二维和三维的数值模拟,详细分析了前缘切口和弧面下反角对翼伞气动性能的影响.结果表明:前缘切口在增强翼伞的滑翔性能的同时,导致升力系数减小,阻力系数增加,且切口越大,升力系数损失越严重;前缘切口的“唇部”可有效降低翼伞型阻;弧面下反角越大,翼伞升力损失越大;所推导的修正LLT(lift line theory)模型,在中小迎角范围内,具有很高的精度.
Two-dimensional and three-dimensional numerical simulations of wingfoils with different leading edge incisions and arcuate anti-angles based on the Clark-Y airfoil are carried out respectively. The results show that: the leading edge incision enhances the parachute glide performance, at the same time it causes the lift coefficient to decrease and the drag coefficient to increase, and the larger the incision, the more serious the loss of lift coefficient; Min “and” min "can effectively reduce the wing parachute resistance; the greater the paraxial angle under the arc, the greater the wing lift loss; the derived LLT (lift line theory) model has a high accuracy .