结合长叶片级S_2流面设计问题的计算结果对大功率汽轮机长叶片气动设计进行了初步的探讨。
Some discussion about aerodynamic design of last stage blade of large steam turbine has been given basing on the result of S_2 design calculation.
研究静气动弹性问题一大关键是要解决流固数据耦合。
Realizing data exchange to reflect coupling between fluid and structures is essential to solving static aeroelasticity problems.
提出了一种数值模拟振动的理想平板绕流场，并提取其气动导数的方法。
Numerical simulation of the flow field around the oscillating ideal flat plate is presented to assess the aerodynamic derivatives.
采用风洞试验和工程计算相结合的方法，对球双锥类外形的稀薄过渡流区气动特性进行了研究。
Experiment and engineering approach have been applied to research aerodynamic characteristics of rarefied transitional flow around sphere-bicone configuration.
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.
本文叙述了具有全动翼的战术导弹出现“反操纵”气动问题，分析其原因及流态，并简要叙述解决办法。
The paper describes the aerodynamical problem of the "anti-control" of tactical missiles with moving-wings, analyses its cause and the flow construction and gives the solution in brief.
为了提高燃气涡轮起动机的功率，了解燃气涡轮设计点的气动参数以及内部流场结构。
It is important to understand aerodynamic parameters of design-point of gas turbine in order to improve the power of gas-starter.
本文描述的是研究爆炸成型发射弹（EFP）模型的流场及超高速空气动力特性所用的弹道试验设备；
The range equipment for the investigation of the hypervelocity aerodynamic properties and flow field of explosively formed projectile(EFP) models is described.
“空气动力学”规定了由于绕流反作用在发射飞行器上存在的压力场和载荷。
"Aerodynamics" defines the pressure fields and loads that exist on a launch vehicle due to the reaction of ambient flow.
基于改进的当地流活塞理论，推导了用模态坐标表示的弹性振动翼面的非定常广义气动力表达式。
Based on the improved local piston theory, this paper presents the matrix expression of generalized aerodynamic forces expressed by the generalized coordinates.
同时，对滑流影响下机身和平尾纵向气动特性的变化机理进行了研究，最后得到了全机气动特性因滑流影响产生的变化。
Combined with the mechanism of slipstream influence on the fuselage and horizontal tail, the paper gives the change in the longitudinal aerodynamic characteristics caused by the slipstream.
通过采用外部声激励的方式，在低速轴流压气机内研究非定常尾流撞击效应对压气机流场结构以及时均气动性能的影响。
Influence of the wake impact effect on the flow field and its average performance in a low speed axial-flow compressor was investigated by using external acoustic excitations.
乘波体是一种由已知超声速或高超声速流场生成的气动构形，在设计点乘波体构型的整个前缘产成贴附的激波。
A wave rider is a configuration designed such that the bow shock generated by the shape is perfectly attached along the leading edge at the design condition.
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.
试验风机的气动性能试验和内部流场可视化与出口流速分布试验的结果彼此吻合。
The performance test results of test fan are in agreement each other with those of internal flow visualization studids and exit velocity distribution test.
实验结果表明：采用最佳倾斜角叶片能降低叶栅能量损失和改善叶栅出口流场的气动性能。
Experimental results show that by using an optimal Angle of inclination energy losses can be reduced and outlet flow fields improved.
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.
首先，文章对列车空气动力学的理论进行了研究，推导出动车周围三维流场的基本控制方程。
Firstly, it studies the theory of train aerodynamics and derives the basic control equation of the three-dim.
亚声速气动力采用面源法计算，高超声速气动力采用修正的牛顿流理论计算。
Panel Method was used for subsonic aerodynamic analysis, and the Modified Newtonian Impact Theory was used for hypersonic aerodynamic analysis.
本论文基于气动光学理论，研究在流场试验中检测高速瞬态流场密度分布的方法与实现。
The paper is based upon Aero-Optics theory, pursuing the methods and realization for measuring the density distribution of transient flow field in wind tunnel test.
德国站的比赛中引入了一种小巧但很有效的空气动力部件——一种新的后部绕流板，原本预期会在匈牙利站比赛中出现的附加的两片后抛翼板在主后翼的下方和后轮前方。
A small but effective aero change introduced in Germany - ahead of a new rear diffuser expected at the next round in Hungary - is this extra flip-up under the main one in front of the rear wheel.
通过壁面静压测量、流场显示及气动探针测量研究了不同掠型叶片组成的平面扩压叶栅特性。
The performance of rectangular compressor cascades composed of different swept blades was studied by static pressure measurement, flow visualization and probe measurement.
基于附着流状态下的旋翼非定常翼型气动模型，给出了计算该状态下的翼型非定常升力、阻力和俯仰力矩的数值计算方法。
A numerical method is given to calculate the unsteady lift, pitching moment and drag acting on an airfoil of rotors under attached-flow conditions in a compressible flow.
高超音速化学非平衡尾迹流场的分析及计算是再入空气动力学的一个重要课题。
The analysis and computation of chemical non-equilibrium hypersonic wakes are important tasks of reentry aerodynamics.
针对气动喷嘴阵列喷气再现线面触觉问题，建立手指皮肤和喷嘴的流固耦合有限元模型。
In view of the line and surface tactility displayed by the pneumatic nozzle array, a fluid-structure coupled finite element model of the finger skin and nozzle was established.
根据叶型表面的压力分布，着重分析了叶型的空气动力绕流和叶栅特性的变化规律。
According to the pressure distribution on the airfoil surface, analysis is made particularly of the airflow around the airfoil and of the variation law of cascade characteristics.
气动换向阀串联流道等效面积计算结果表明，不同通道之间的等效面积差别为8.9%，可见各流道结构参数没有得到合理匹配。
The effective areas of the serial passage in one of the valve were calculated. It is found that the difference is 8.9% between different passages.
本文将传统的螺旋桨动量理论与计算流体力学的方法相结合，数值模拟螺旋桨滑流对其后部件气动特性的影响。
This thesis concentrates on the application of CFD techniques to simulate the effect of turbo-propeller slipstream on the parts behind the propeller.
各运动规律中，阻流门气动载荷在阻流门开始转动瞬间加载。
For all kinetic schedules, aerodynamic load on blocker doors increases sharply once it starts operation.
通过地面试验和高超声速非平衡流的研究，取得了再入突防气动物理的重要进展。
Through ground test and hypersonic flow research, he made great progress in air-breathing hypersonic technology.
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