This paper describes the advance of fighter's flying qualities researching at high Angle of attack a.
叙述了战斗机大迎角飞行品质研究的进展情况。
The influence on flow structure and aerodynamic of a slender by sweep wing at high Angle of attack was studied.
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 extended linearization of nonlinear systems is used to design flight control systems at high angle of attack.
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 experimental investigation of the effect of winglet on the spatial vortex of slender body at high Angle of attack is presented.
本文介绍了小翼对旋转体空间涡影响机理的实验研究结果。
Dynamic aerodynamics characteristic is one of very important parameters of modern maneuverable aircraft to be scaled at high Angle of attack and high speed.
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。
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.
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。
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.
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。
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.
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。
Complex wave structures of supersonic inlet at different Angle of attack and spinning velocity related to high speed spinning and critical status were achieved.
得到了高速旋转工况下对应于不同来流攻角和旋转角速度，临界工况时，超声速进气道内外流场复杂的波系结构。
Complex wave structures of supersonic inlet at different Angle of attack and spinning velocity related to high speed spinning and critical status were achieved.
得到了高速旋转工况下对应于不同来流攻角和旋转角速度，临界工况时，超声速进气道内外流场复杂的波系结构。
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