在低雷诺数条件下，对于纯俯仰运动，随着翼型厚度的减小，平均阻力系数也变小。
For pure pitching motion, the results show that average drag coefficient decreases as airfoil thickness is reduced.
超音速飞机的长窄三角翼型设计是美观实用原则的代表，极度的流线型设计对于将阻力降到最低是必要的。
The long narrow delta shape of supersonic aircraft is an example of aesthetic functionalism, an extreme form of streamlining that is essential to minimize drag.
由于前缘涡的影响，翼型厚度增加，平均压差阻力系数变小，甚至会出现负值。
As airfoil thickness is increased, the average pressure drag, affected by leading edge vortex is reduced even to be negative, and meanwhile friction has little increase.
基于附着流状态下的旋翼非定常翼型气动模型，给出了计算该状态下的翼型非定常升力、阻力和俯仰力矩的数值计算方法。
A numerical method is given to calculate the unsteady lift, pitching moment and drag acting on an airfoil of rotors under attached-flow conditions in a compressible flow.
高速飞机通常采用低阻力、低升力的流线型薄翼型，载重量大的低速飞机使用高阻力、高升力的厚翼型。
High-speed aircraft usually employ thin, low-drag, low-lift airfoils; slow aircraft that carry heavy loads use thicker airfoils with high drag and high lift.
同时进行了单段翼型跨音速降低激波阻力的优化设计。
And optimization computation for reducing drag of Shockwave of single airfoil in transonic flow is also successful.
在亚跨声速时分别采用了表面积分和尾迹积分求得给定翼型RAE2822的阻力。
Predicted drag values for a given airfoil(RAE2822 airfoil)were compared and discussed using the surface integration and wake integration methods under both subsonic and supercritical flow conditions.
在平面形状优化基础上，在机翼容积不变约束下，再采用剖面翼型优化设计，通过机翼剖面细微变化弱化较大马赫数下的激波、减小激波阻力。
In the second design step, improvement of wing's aerodynamic characteristic is mainly depended on the weakening of shock which reduces wave drag during the wing section optimization.
在平面形状优化基础上，在机翼容积不变约束下，再采用剖面翼型优化设计，通过机翼剖面细微变化弱化较大马赫数下的激波、减小激波阻力。
In the second design step, improvement of wing's aerodynamic characteristic is mainly depended on the weakening of shock which reduces wave drag during the wing section optimization.
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