用速度梯度、压力梯度和环量梯度模拟大攻角尖前缘三角翼流场。
Velocity gradient, pressure gradient and circulation gradient are used to model the separated vortex flow field over a leading edge delta wing.
在材料硬化阶段，含层间裂纹的层板裂尖前缘应力奇异性总是存在的；
The numerical results indicate that FEM is efficient to analyze stress singularity, and the stress singularity always exists in the hardening phase …
计算模型包括尖前缘、菱形前缘、圆形前缘等三种不同前缘形状的机翼。
Numerical investigation of the effects of different leading-edge profiles on vortical flows over a double-delta wing;
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 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.
本文介绍了尖前缘翼诱导激波和湍流边界层干扰流场壁面特性，着重强调马赫数影响。
This paper presents the surface characteristics of the inter-action between shock wave and turbulent boundary layer induced by sharp fin with emphasis on Mach number effects.
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。
This method may be used to calculate the arbitrary airfoils with sharp leading edge provided that the shock wave is attached.
与今天使用的典型机翼相比，SUGARVolt的机翼的翼尖相距更远，前缘与后缘之间相距更短，并且后掠角更小。
Compared to the typical wing used today, the SUGAR Volt wing is longer from tip to tip, shorter from leading edge to trailing edge, and has less sweep.
高超声速气流条件下，尖楔前缘的热环境非常恶劣。
The thermal environment of the wedge leading edge is rigorous in hypersonic flow.
次要结构由机翼前缘，后缘和翼尖构成，主要用来减小空气阻力，支撑蒙皮，协助飞行操纵面和操纵机构。
The secondary structures, which support aerodynamic fairings or skins, flight control surfaces and control mechanisms, consist of the leading edge, trailing edge, and wingtip.
次要结构由机翼前缘，后缘和翼尖构成，主要用来减小空气阻力，支撑蒙皮，协助飞行操纵面和操纵机构。
The secondary structures, which support aerodynamic fairings or skins, flight control surfaces and control mechanisms, consist of the leading edge, trailing edge, and wingtip.
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