对不同布局的总压恢复系数进行比较，颌下及两侧进气则较头部进气有好的攻角特性。
By comparison of inlet total pressure recovery coefficient, attack-angle performance of chin inlet and two-dimensional inlet are superior to frontal inlet.
运用数值方法模拟了细长体在不同攻角条件下亚音速绕流的背涡结构，探讨了非对称涡流的气动力特性。
Subsonic vortical flows over a slender body at different angles of attack were simulated numerically, and the aerodynamic characteristics of asymmetric vortical flow were also investigated.
根据计算结果对大负攻角条件下叶栅二维分离流动的特点以及攻角对叶栅气动特性的影响进行了分析。
According to the obtained results, the behavior of the separation flow and the effects of negative incidences on the aerodynamic characteristics of cascade are analyzed.
为此，设计了大攻角旋转天平支撑系统，此系统可测定飞机模型在不同姿态角下绕风轴以一系列恒定的角速率旋转时的气动特性。
The paper has introduced design of the support system for rotary balance of high attack angle, and the importance and methods of studying spin of aircraft.
可用来计算有攻角、侧滑角、滚转角的非对称体的气动特性。
The methods are devoted to determining aerodynamic performances for asymmetrical body with Angle of attack, Angle of side slip and roll Angle.
对一种轴对称形式的高超声速飞行器全流道开展了风洞实验和数值模拟研究，分析了不同来流总压、飞行攻角全流道的流场结构和气动力特性。
This paper presents a numerical simulation of separated flow over an airfoil at large attack angles with oscillating excitations to study separation flow control over an airfoil.
通过气弹模型风洞试验，研究了不同间距、风偏角、风攻角及固有频率下，串列主缆间的气动干扰特性。
The basic aerodynamic interference of tandem cables was investigated through a series of aeroelastic model wind tunnel tests.
双三角翼气动布局比三角翼飞机具有更好的大攻角空气动力特性。
The effects of Gurney flap on double delta wing aerodynamic performance in low speed wind-tunnel tests;
双三角翼气动布局比三角翼飞机具有更好的大攻角空气动力特性。
The effects of Gurney flap on double delta wing aerodynamic performance in low speed wind-tunnel tests;
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