The horn location on airfoil surface has the most severe effects on airfoil coefficients.
翼型表面积冰位置变化对气动系数影响最大；
Although it is very small in size, some developments in the test section of pressure distribution on airfoil surface have been attempted.
尽管该风洞的尺寸很小，我们仍对翼型表面压力分布试验段的研制工作进行了大胆的尝试。
According to the pressure distribution on the airfoil surface, analysis is made particularly of the airflow around the airfoil and of the variation law of cascade characteristics.
根据叶型表面的压力分布，着重分析了叶型的空气动力绕流和叶栅特性的变化规律。
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。
Surface pressure distribution can be used to describe the airfoil boundary layer flow well.
可用于表面压力分布以及描述翼型边界层流的。
The stall of the wing occurs at the highest lift coefficient on an airfoil, when the airflow can no longer go around the airfoil's nose (leading edge) and separates from the upper wing surface.
机翼失速的发生在电梯表面系数最高的机翼上，当气流不能继续围绕翼型的鼻子(领先)，并脱离机翼上。
The results indicate that passive control technique can reduce peak Mach number on the surface of the airfoil and reduce the adverse pressure gradient, shock is also weakened.
结果表明，被动控制使得沿模型表面的马赫数峰值及过压力梯度明显减小，激波减弱。
In the aerodynamics domain, the time-dependant aerodynamic force on the surface of the airfoil is computed by solving the unsteady Reynolds averaged Navier-Stokes equation.
在流体域的动网格上，通过求解非定常的雷诺平均N - S方程，计算出翼型表面的非定常气动力。
Simulation experiments have been made on the hydrodynamic characteristic of the lifting airfoil moving near the sea surface.
对接近海面运动的升力翼的水动力特性进行了模拟试验。
An optimization method is used to obtain deflection Angle of control surface and the aerodynamic efficiency of airfoil is calculated.
用数值优化方法取得自适应翼型最优的舵面偏角，并计算其气动特性。
The aerodynamic characteristics of an airfoil with a jet issuing from its lower surface are investigated by numerical method.
应用数值方法模拟了飞行器升力面下表面喷气的增升作用。
The leading edge portion includes a plurality of staggered holes for causing fluid to flow over a surface of the airfoil portion.
该前缘部包括多个错开的孔以便使流体在该翼面部的表面上流动。
The leading edge portion includes a plurality of staggered holes for causing fluid to flow over a surface of the airfoil portion.
该前缘部包括多个错开的孔以便使流体在该翼面部的表面上流动。
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