叙述了战斗机大迎角飞行品质研究的进展情况。
This paper describes the advance of fighter's flying qualities researching at high Angle of attack a.
计算了旋成体大迎角涡流和带底部喷流的绕流场。
Numerical investigation of base jet interaction in a supersonic external flow;
设计了模型和实验装置，进行了大迎角低速风洞实验。
The experimental model and equipment are designed, and the low speed wind tunnel experiment at high angles of attack is made.
研究了在大迎角下，后掠翼对细长体绕流结构和气动力特性的影响。
The influence on flow structure and aerodynamic of a slender by sweep wing at high Angle of attack was studied.
在水洞中研究了三翼面流动分离和三翼面布局飞机大迎角的流动机理。
The flow visualization and measurement technology were used to study the flow separation, development of mass vortex and flow control mechanism of triplane at large angle of attack in a water tunnel.
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。
Numerical results show that contribution of high order terms are very important at lower Mach number or high angles of attack.
高速大迎角动态气动特性是衡量新一代高机动飞行器性能的重要参数之一。
Dynamic aerodynamics characteristic is one of very important parameters of modern maneuverable aircraft to be scaled at high Angle of attack and high speed.
利用非线性系统的扩展线性化方法设计具有大迎角的非线性飞行控制系统。
The extended linearization of nonlinear systems is used to design flight control systems at high angle of attack.
采用测压方法研究了矢量喷流对细长旋成体大迎角非对称流动的影响特性。
This paper studies the effect of vectoring jet on the transverse aerodynamic characteristics of a slender body.
试飞结果表明，JL8飞机具有良好的大迎角特性及低速和高速失速特性。
The results of flight test show that JL8 aircraft has very good characteristics of high Angle of attack, low speed and high speed stalls.
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。
Aeroelastic analysis at high angles of attack is an attractive and complicated research subject in modern aircraft design.
有侧滑时，尖侧缘的非圆截面机身头部在中等和大迎角下，可具有方向稳定性。
The fore-body with sharp section angle can produce direction stability at middle-higher angle of attack in the case of side-slip.
结论：针刺内大迎治疗中风后舌体运动障碍的疗效肯定，明显优于传统针刺组。
Conclusions: the therapeutic effect of the treatment group was superior to that of the control group on treatment for Tongue Dyskinesia Post Stroke.
飞机或导弹在大迎角下飞行时会形成非对称涡，从而产生很大的侧滑力和偏航力矩。
When a fighter aircraft or missile flies at high angle of attack(AOA), asymmetric vortexes are produced from the forebody and induce strong side force and yawing moment.
在跨声速风洞中研究了声激励对于可压缩流中细长旋成体大迎角流动非对称性的影响效果。
The effect of acoustic excitation on the flow asymmetry over a slender body in compressible flows was investigated in a transonic wind tunnel.
研究表明：MEMS器件对控制大迎角细长旋成体非对称涡和复杂流场具有良好的控制能力。
The research indicated that MEMS device generate excellent control effect on asymmetric vortices over slender body as well as on complex flow field.
本文介绍用低超声速喷管代替声速喷管，解决了大迎角大堵塞度跨声速实验时的风洞壅塞问题。
Instead of the sonic nozzle, low supersonic nozzles have been utilized to solve the choking problem in transonic wind tunnel testing of high angle-of-attack and high blockage.
采用数值模拟求解NS方程方法计算与分析了绕大钝头短体外形的跨音速大迎角时的湍流流动。
The transonic turbulent flow around a blunt nosed and short body at large angle of attack was calculated and analysed by using numerical simulation method to solve the full N S equations.
它能控制气流分离和减小大迎角时的阻力，提高抖振边界和降低抖振强度，改善大迎角的飞行品质。
They also can expand the buffet boundary and decrease the buffet intensity. As a result, the large angle-of-attack flying quality can be significantly improved by utilization of maneuvering flaps.
为了研究飞行器在纵向大迎角状态下的动态失速现象，设计了一套用于低速风洞的升沉振动测量装置。
In order to study dynamic stall phenomena of an aircraft in portrait at a high Angle of attack, designing a measuring device of heave oscillation for a low speed wind tunnel.
本文就如何处理尾迹区的测压数据来确保阻力测量的精确度及如何测出大迎角的阻力特性进行了一些探讨。
This paper introduces a process method of the pressure data in the wake to obtain the drag characteristics with high accuracy, and discusses about the drag measurement at high Angle of attack.
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.
本文就如何处理尾迹区的测压数据来确保阻力测量的精确度及如何测出大迎角的阻力特性进行了一些探讨。
This paper introduces a process method of the pressure data in the wake to obtain the drag characteristics with...
本文就如何处理尾迹区的测压数据来确保阻力测量的精确度及如何测出大迎角的阻力特性进行了一些探讨。
This paper introduces a process method of the pressure data in the wake to obtain the drag characteristics with...
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