考虑了不同飞行攻角、不同燃料流率下气动参数，包括升力系数、阻力系数和俯仰力矩系数的变化规律。
The change rules of aerodynamic parameters including lift coefficient, drag coefficient and pitch moment coefficient have been analyzed when Angle of attack and fuel flow rate is changed.
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.
基于扇翼机的飞行原理，提出通过改变攻角以及增加尾部升力面弦长的方式提高气动效率，进而实现垂直升降的方法。
Based on the principle of flight of fan wing aircraft, realizing methods of VTOL are preposed by changing the Angle of attack and increasing chord length of the tail.
在零攻角实验时不同模型的空气动力阻力是采用简化方法来计算的；
The aerodynamic drag of different models at zero angle of attack in the experiment is calculated using the simplified procedure.
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.
本文概述最初阶段利用风洞试验数据应用模糊逻辑研究飞机大攻角空气动力学的情况。
In this paper, the initial stage in application of fuzzy logic to aircraft high-Angle-of attack aerodynamics using wind tunnel test data is outlined.
高空风引起的气流攻角对火箭飞行中的气动载荷和飞行环境有较大的影响。
There is a larger effect of flow Angle of attack caused by high altitude wind on aerodynamic load and flight environment in rocket flighting.
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.
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.
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.
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;
对我国开展大攻角气动问题研究的技术途径提出了一些建议。
Finally, some Suggestions about technical approaches to study high-angle-of...
对我国开展大攻角气动问题研究的技术途径提出了一些建议。
Finally, some Suggestions about technical approaches to study high-angle-of...
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