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structure influence coefficient method    
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  结构影响系数法
    It is solved based on Euler/N-S equations with cell-centered finite-volume algorithm. The structure deformation is calculated by a structure influence coefficient method. We use a triangle area weight method and a constant volume transformation(CVT) method to solve the fluid-structure interaction problem.
    在C-H网格的基础上,采用Jam eson的中心差分有限体积法求解Eu ler/N-S方程,采用结构影响系数法计算结构的弹性变形,用三角元面积加权法和常体积转换法(CVT)实现流固耦合,计算了弹性后掠机翼在跨音速状态的静气动弹性问题
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  结构影响系数法
    It is solved based on Euler/N-S equations with cell-centered finite-volume algorithm. The structure deformation is calculated by a structure influence coefficient method. We use a triangle area weight method and a constant volume transformation(CVT) method to solve the fluid-structure interaction problem.
    在C-H网格的基础上,采用Jam eson的中心差分有限体积法求解Eu ler/N-S方程,采用结构影响系数法计算结构的弹性变形,用三角元面积加权法和常体积转换法(CVT)实现流固耦合,计算了弹性后掠机翼在跨音速状态的静气动弹性问题
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In order to study in depth the static aeroelastic characteristics of supercritical wing,we present the analysis method we developed.The feature of our analysis method is that we employ Euler equations for aerodynamic calculations.As usual,our analysis method involves the calculation of aerodynamic loads followed by calculation of deformation;this cycle is repeated again and again until the actual aerodynamic loads and the actual deformation of wing are both obtained.The aerodynamic loads are calculated by solving...

In order to study in depth the static aeroelastic characteristics of supercritical wing,we present the analysis method we developed.The feature of our analysis method is that we employ Euler equations for aerodynamic calculations.As usual,our analysis method involves the calculation of aerodynamic loads followed by calculation of deformation;this cycle is repeated again and again until the actual aerodynamic loads and the actual deformation of wing are both obtained.The aerodynamic loads are calculated by solving Euler equations with a finite volume algorithm based on center difference;the structure deformation is calculated by structure influence coefficient method.We take a swept-back wing as numerical example and the numerical simulation results obtained with our method show preliminarily that our method is feasible.We also calculate the static aeroelastic deformation for three wings(swept back wing,straight wing,forward swept wing) that adopt supercritical airfoil(RAE2822) or general airfoil(NACA0012 or NACA64A006) with total lift unchanged;we find that the center of rigidity for the forward swept wing is at the 40.0% of chord,the pressure center for the general-airfoil NACA0012 wing is at the 26.1% of chord,the pressure center for the supercritical-airfoil wing is at the 50.4% of chord.Obviously,the pressure center of supercritical wing shifts backwards;this is the main reason why pitching up deformation of supercritical wing is less than that of general wing.

采用三维Eu ler方程为控制方程,计算机翼所受的气动力与静气动弹性平衡方程耦合求解,研究超临界机翼的静气动弹性规律,并以超临界弹性机翼和普通弹性机翼为算例,计算弹性飞机飞行中的真实载荷和扭转变形,并在已知弹性机翼飞行时总载荷保持不变的情况下,确定超临界机翼结构弹性在飞行中对载荷的影响。

The characteristics of static aeroelasticity for elastic wings are calculated by using H-C type grid.It is solved based on Euler/N-S equations with cell-centered finite-volume algorithm.The structure deformation is calculated by a structure influence coefficient method.We use a triangle area weight method and a constant volume transformation(CVT) method to solve the fluid-structure interaction problem.We take a swept-back wing as a numerical example to simulate the transonic aeroelastic...

The characteristics of static aeroelasticity for elastic wings are calculated by using H-C type grid.It is solved based on Euler/N-S equations with cell-centered finite-volume algorithm.The structure deformation is calculated by a structure influence coefficient method.We use a triangle area weight method and a constant volume transformation(CVT) method to solve the fluid-structure interaction problem.We take a swept-back wing as a numerical example to simulate the transonic aeroelastic problem.

在C-H网格的基础上,采用Jam eson的中心差分有限体积法求解Eu ler/N-S方程,采用结构影响系数法计算结构的弹性变形,用三角元面积加权法和常体积转换法(CVT)实现流固耦合,计算了弹性后掠机翼在跨音速状态的静气动弹性问题

 
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