Increasing the lift drag ratio of turbine blade is an effective way for improving turbines aerodynamic characteristics. 提高叶轮机械叶片的升阻比(L/D),是改进叶轮机械气动性能的重要途径。
We put stress upon investigating the effect of changing lift drag ratio and reentry angle on reentry orbit. 着重研究了改变升阻比(L/D)和再入角对再入轨道的影响。
Under some condition, Gurney flap can increase lift coefficient and lift drag ratio of the airfoil. 在一定的条件下,Gurney襟翼可以明显增加翼型的升力系数但不过多增加阻力系数。
To enhance the roughness of the blade's partial area for increasing the lift drag ratio, a new method was given in this paper. 该文给出了一种提高叶栅叶片的升阻比(L/D)新措施,即采用加大叶片局部粗糙度来提高叶片的升阻比(L/D)。实验研究证实这种方法确实有效。
Finally, the results proved that increasing the roughness of the wind turbine blade airfoil trailing edge can improve the lift coefficient and lift drag ratio coefficient in some condition. 最后,对风力机专用叶型进行的叶片表面局部增加粗糙度的风洞实验,结果证明了在叶片压力面尾缘通过适当增加一定宽度、一定粗糙度的粗糙带可以增大叶片的有效升力系数。