在跨音速马赫数范围内需要经验结果。
本文研究了机翼跨音速颤振的频域计算方法。
Computation of wing flutter for unsteady transonic flows in the frequency domain is studied in this thesis.
进行了多级跨音速风扇粘性流动的数值模拟研究。
Numerical simulation of viscous flows through multistage transonic fans was carried out.
其结论对改善跨音速风洞设计和模型试验是有用的。
The conclusions believed to be useful to improve the design of transonic wind tunnel and model tests.
同时进行了单段翼型跨音速降低激波阻力的优化设计。
And optimization computation for reducing drag of Shockwave of single airfoil in transonic flow is also successful.
本文提出了求解跨音速欧拉方程的一种隐式时间推进法。
An implicit time-marching method is presented for solving the transonic Euler equations.
本文采用迭代求解的方法计算弹性机翼的跨音速压强分布。
An iteration method is used for computing the transonic pressure distribution on a flexible wing.
本文考虑轴对称跨音速进气道外流场的有限差分计算方法。
A finite difference method for computing the axisymmetric, transonic flows over nacelle is presented in this paper.
为论证方法的有效性，给出了几个跨音速涡轮叶栅的计算结果。
Several computed results of transonic turbine cascades are presented to illustrate the method's capabilities.
使用跨音速非定常空气动力，对扑动间隙和旋转间隙进行研究。
Flapping and rotary gap have been investigated with the help of transonic unsteady aerodynamic forces.
本文运用赝势函数变域变分有限元方法进行了跨音速翼型设计。
The variational of finite element method(FEM) using the pseudo-potential function is presented to design the airfoil shape of transonic rotational flows.
分别对可压缩叶栅流场的亚音速和跨音速流动进行了数值模拟计算。
Some cases of compressible flow as well as incompressible flow are presented.
本文给出了基于有限面积法的跨音速透平叶栅速度面反问题设计方法。
This paper deals with the inverse design problem of transonic turbine cascade in the hodograph plane by the finite area method.
从全速位方程出发研究了机翼和翼身融合体跨音速绕流的有限元算法。
The finite element algorithm for transonic flows about wing and blended wing-body configuration is investigated based on the full potential equations.
本文对模型周围的侧壁附面层抽吸，研究跨音速二元风洞的侧壁干扰。
This paper presents an investigation on the side wall effect in two -dimensional transonic wind tunnel with sidewall boundary layer suction around the model.
本文运用赝势函数变分有限元方法数值模拟了绕翼型的跨音速有旋流动。
The variation finite element method (FEM) using the pseudo-potential function was presented for the simulation of transonic rotational flows.
计算结果表明，本方法是透平机械内部跨音速流动计算的强有力的手段。
Using the improved method we studied inviscid and viscous transonic flow in turbomachinery based on Euler and Navier Stokes equations.
由于在跨音速流场内可能存在激波，所以也导出了流线座标系二维激波关系式。
And the two-dimensional shock-wave relations of the stream-line coordinates are also derived as the shock wave may be exist in transonic flow field.
本文采用近似因式分解(AF 2)方法，数值求解二元跨音速小扰动速势方程。
An implicit approximate factorization scheme (AF2) is employed in this paper to obtain the numerical solutions of TSD and TSTD equation.
本文给出了在跨音速流动中，计算三维机翼非定常载荷分布的核函数法和计算结果。
A kernel function method and the results of computing unsteady load on three-dimensional wings in transonic flow are presented in this paper.
增压连续式跨音速风洞在我国尚属首例，是具有国际先进水平的大型高速翼型风洞。
Pressurizing, continuous and transonic wind tunnel is the first one in our country, and it is the world ' s first class tremendous high - speed aerofoil wind.
增压连续式跨音速风洞在我国尚属首例，是具有国际先进水平的大型高速翼型风洞。
Pressurizing, continuous and transonic wind tunnel is the first one in our country, and it is the world's first class tremendous high - speed aerofoil wind.
给出一种新的二维跨音速柔性自适应壁风洞实验迭代方案，计算方法和实验验证结果。
In this paper, a new iterative testing strategy is described for two dimensional model testing in transonic flexible adaptive walled wind tunnel and wall adjustment computing method.
低能量损失系数跨音速透平叶栅的设计和实现是提高跨音速透平性能的关键问题之一。
The design and realization of a transonic turbine cascade with low energy loss is one of the crucial problems which should be solved for designing good transonic turbines.
气水模拟方法对跨音速叶栅的方案设计和定性分析具有正确、直观、简便、经济的优点。
The shallow water through analogy has advantages of exactness, visualization, simplicity and economy valuable in the concept design and qualitative analysis stage of transonic turbine cascades.
本文为NACA0012翼型在NH - 1风洞进行跨音速二维测压实验的研究报告。
This paper is a report of experimental pressure. Measurement research for NACA0012 airfoil in NH-1 transonic wind tunnel.
使用FLUENT软件对某型跨音速涡轮叶栅的导叶进行了S_1流面的粘性流动计算。
The present paper computed the viscous flow of S_1 flow surfaces in some transonic turbine vane cascade by using the computational software FLUENT.
二维跨音速叶栅流场的计算是在无粘时间相关法计算程序的基础上采用无粘-边界层迭代而得。
An inviscid-viscous interaction method based on the inviscid time marching computer code has been employed to calculate the transonic flow field of two dimensional cascade.
文中还提出了压气机叶栅在高亚音速、跨音速工作条件下，修正气体压缩性影响的新的图线方法。
In this paper, a new curvilinear method for correcting the gaseous compressible effect under higher subsonic and transonic intake condition upstream of the cascade is. presented.
文中还提出了压气机叶栅在高亚音速、跨音速工作条件下，修正气体压缩性影响的新的图线方法。
In this paper, a new curvilinear method for correcting the gaseous compressible effect under higher subsonic and transonic intake condition upstream of the cascade is. presented.
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