超临界机翼静气动弹性特性研究  

An Analysis Method of Static Aeroelastic Characteristics of Supercritical Wing

作　　者：闫锋[1] 杨青[1] 杨永年[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,陕西西安710072

出　　处：《西北工业大学学报》2005年第6期733-736,共4页Journal of Northwestern Polytechnical University

摘　　要：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。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.

关 键 词：EULER方程 静气动弹性 超临界弹性机翼 弹性机翼 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]