Aerodynamic sensitivity for subsonic lifting-surface with arbitrary curved leading edge is evaluated by kernal function method.
具有任意曲线前缘的亚音速升力面的气动敏感性导数由核函数法给出。
This method may be used to calculate the arbitrary airfoils with sharp leading edge provided that the shock wave is attached.
在激波附体的条件下，本文的方法可用于计算大迎角尖前缘任意翼型的超音速和高超音速俯仰安定性导数。
In this paper, separation control on Joukowsky airfoil having leading edge rotational cylinder is investigated by numerical simulation method.
本文使用数值模拟方法研究了活动翼面对翼型背风面分离的控制作用。
The finite volume method was used to compute the aerodynamic load, and the effect of leading-edge cut and ribs on the pressure distribution was analyzed simultaneously.
使用有限体积法计算了飞行时的气动载荷，分析了前缘切口和翼肋开孔对压强分布的影响；
A method for forming the leading edge portion using refractory metal core technology is described.
对使用耐热金属芯工艺制出该翼面部的方法予以说明。
In this paper, an approximate analytical method is developed by which pitching derivatives are predicted for three dimensional wings with pointed leading edge in supersonic and hypersonic stream.
本文给出计算超声速和高超声速尖前缘三维机翼俯仰导数的一个近似解析方法。
In the nuclear signal time analysis, it is a common method of using the leading edge timing error analysis.
在核信号时间分析中，前沿定时误差分析是常用的方法。
In the nuclear signal time analysis, it is a common method of using the leading edge timing error analysis.
在核信号时间分析中，前沿定时误差分析是常用的方法。
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