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细长翼在迎角稍大时,前缘卷起螺旋状分离涡,使上表面压力降低,升力增加。涡襟翼技术也是利用前缘涡的这一特性提高升阻比的。为计算有分离涡的机翼特性,须研究分离涡层的卷起和涡层之间相互干扰的计算方法。早期Brown和Michael,Smith等在锥形流假设下,应用细长体理论计算过三角翼的气动特性。Sack和尹协远等放弃锥形流假设,用离散涡代替脱体涡层,但仍用保角转绘法处理横流面内绕翼面流动。这类方法对横截面形状较复杂的细长翼(如带涡襟翼的机翼),因转绘函数复杂,计算困难。本文为避免转绘带来的困难,采用直接布涡法计算有分离涡的机翼气动特性。
When the slender wing is slightly larger at the angle of attack, the leading edge turns spiral separation vortex so that the pressure on the upper surface decreases and the lift increases. Vortex flap technology is also the use of leading edge vortex characteristics to improve the lift-drag ratio. In order to calculate the wing characteristics of a separate vortex, the method of calculating the roll-up of the separated vortex and the mutual interference between the vortices must be studied. Early Brown and Michael, Smith et al. Used the theory of the slender body to calculate the aerodynamic characteristics of the delta wing under the assumption of conical flow. Sack and Yin Xieyuan gave up the conical flow hypothesis, using discrete vortices instead of shedding vortices, but still using conformal mapping to deal with the flow around the airfoil in the cross-flow surface. Such methods for elongated cross-sectional shape of the wing (such as wings with vortex flaps), due to complex drawing functions, calculation difficulties. In order to avoid the difficulty of drawing, the direct vortex method is used to calculate the aerodynamic characteristics of the wings with separate vortices.