有限翼展机翼

利用STF元件（后掠梯形一旗形插入件）的自激振荡组件系统特性和有限翼展机翼特性进行了管内紊流强化换热的研究。

STF ( Sweptback Trapezoid Flag ) type dynamic insert in the characters of self excitation oscillation and finite span wing is used to enhance the turbulent heat transfer .

本文提供了亚音速升力面理论的一种新解法，可求解亚音速流中有限翼展机翼的载荷分布。

A new method based on lifting-surface theory is presented determining the load distributions on finite wings in subsonic flows .

从三维时间相依可压缩边界层动量积分方程和平均流动能积分方程出发，将二维可压缩层、湍流边界层积分方程算法推广到求解有限翼展后掠机翼的边界层流动。

Based on three-dimensional , time-dependent momentum and mean-flow kinetic energy integral equations for compressible boundary Layers in nonorthogonal curvilinear coordinates , the existing algorithm for two-dimensional , compressible , Laminal and turbulent integral equations is extended to solve the boundary-layer problem over finite swept wings .