The unsteady motion of a two-dimensional thick airfoil at high angles of attack is considered in this paper.
本文研究二维厚度翼型的大攻角非定常运动。
Aeroelastic analysis at high angles of attack is an attractive and complicated research subject in modern aircraft design.
大迎角气动弹性分析是现代飞行器设计中非常引人瞩目并且复杂的研究课题。
The experimental model and equipment are designed, and the low speed wind tunnel experiment at high angles of attack is made.
设计了模型和实验装置，进行了大迎角低速风洞实验。
Numerical results show that contribution of high order terms are very important at lower Mach number or high angles of attack.
数值结果表明高阶项的贡献在较低马赫数或大迎角情况下是很重要的。
Both these sections are unique and developed specifically for maximum effectiveness at low speeds and at high angles of attack.
这两个部分是独一无二的，专为开发成效最大，在低速和高攻角。
TAIL DESIGN : The STOL CH 801 tail sections are designed to provide maximum effectiveness (control) at slow speeds and at high angles of attack.
尾部设计：甲烷的短距起降801尾节的目的是提供在高攻角的最大效益（控制）的速度和缓慢。
The conclusion is that the key to raise the experimental accuracy lies in reducing and correcting the systematic errors due to blockage effect at high angles of attack.
结论是：提高大攻角实验数据准确度的关键在于减少和修正由于阻塞效应引起的系统误差。
The agility of aircraft with conventional linear flight controllers tends to drop rapidly under high angles of attack, and kinematic coupling of motions furtherly promotes the tendency.
带传统线性控制器飞机在大迎角高机动飞行时敏捷性明显地减小，运动状态严重耦合更加重这一趋势，而此时操纵能力往往仍有剩余而却未能被利用。
Based on traditional support system in wind tunnel testing, the combination support system measuring support interference on high angles of attack model in low speed wind tunnel was designed.
基于传统的风洞试验支撑设备，设计了用于低速风洞测量大攻角模型支架干扰的组合支撑设备。
This paper deals with the numerical solution of the Euler equation for airfoils using approximate boundary conditions and the effects dorsal fin on vortex over delta wing at high angles of attack.
本论文主要是通过实验来研究细长圆锥体在大迎角下的绕流流场的特性和细长三角翼加背鳍后对前缘涡的影响，检验相关理论结果。
It is shown the nonlinear aerodynamic model given by the article can accurately calculate aerodynamic responses of aircraft models in large amplitude forced oscillation tests at high angles of attack.
实际计算结果表明该非线性气动力模型能够较为精确地计算飞机模型大幅值迎角简谐振动产生的气动力响应。
A robust iterative method suitable for the numerical simulation of vortex flows at high angles-of-attack is established based upon the multiple line-vortex model (MLVM).
基于多重线涡模型（MLVM），本文建立了一种计算机时少、收敛性强的适用于大迎角涡流势流数值模拟的迭代算法。
A robust iterative method suitable for the numerical simulation of vortex flows at high angles-of-attack is established based upon the multiple line-vortex model (MLVM).
基于多重线涡模型（MLVM），本文建立了一种计算机时少、收敛性强的适用于大迎角涡流势流数值模拟的迭代算法。
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