The unsteady flow field near the leading edge of an oscillating sweptback wing is obtained by using 3-D subsonic liftingsurfacetheory.
本文应用三元亚音速升力面理论求出了后掠翼前缘附近的流场。
2
A numerical method is presented for prediction of propeller performance and pressure distribution on blade surface according to liftingsurfacetheory.
本文提供了一种根据升力面理论计算螺旋桨桨叶表面压力分布和螺旋桨性能的数值方法。
3
The span wise coherence function of the aerodynamic lifting force in the buffeting response of bridges is analyzed by using the liftingsurfacetheory of airfoils.