摘要
对一架巡航马赫数为1.41的斜置飞翼大型超音速客机进行了气动设计,包括翼型设计以及机翼模型的生成。采用翼型参数化控制方法调整机翼的平面形状、扭转、弯曲和厚度分布,使机翼具有一个近似的椭圆载荷分布和Sears-Haack面积分布。通过研究升力系数和后掠角对斜置飞翼升阻比的影响,得到一个无黏的最佳设计结果。
An oblique flying wing with a cruise mach number of 1.41 is designed. It includes the design of the airfoil sections and a blending of these airfoil sections to create the wing. Using a parameterized airfoil shape generator, a careful tailoring of the wing planform and planform bending, twisting and wing thickness distribution are used to ensure a nearly elliptic load distribution and a minimum drag body area distribution. The lift coefficient and wing sweep are varied sequentially to arrive at an optimum inviscid design.
出处
《科学技术与工程》
2009年第10期2663-2668,共6页
Science Technology and Engineering
关键词
斜置飞翼
气动设计
最小阻力体
oblique flying wing aerodynamic design minimum drag bodies
