摘要
本文在非结构网格基础上,以Euler方程为控制方程,耦合结构静平衡方程,采用结构影响系数法,发展了一种静气动弹性时域计算方法。首先本文采用该方法对中等展弦比后掠机翼的静气动弹性变形进行了计算,结果表明本文采用的气动力计算方法,计算结果与参考文献提供的结果及实验结果吻合良好,静气动弹性计算方法可行。然后本文采用该方法对超临界机翼和普通机翼的静气动弹性变形进行了求解,并对计算的结果进行了对比分析,总结出一些超临界机翼静气动弹性变化规律,为超临界弹性机翼的设计、提高超临界弹性机翼的气动特性提供了一些理论依据。
Coupling with static aeroelastic balancing equation, the time domain calculation method of static aeroelastic deformation is developed using the structure influence coefficient method. Firstly, the static aeroelastic deformation of medium aspect ratio swept-back wing was simulated using the developed method. Computational results are in good agreement with those of other literatures and experimental results. The static aeroelasticity calculation method is feasible. Then, the aerodynamic force of supercritical wing and common wing is calculated by 3-D Euler equations with cell-centered finite-volume algorithm, explicit Runge-Kutta time stepping scheme. The static aeroelasticity characteristics of supercritical wing are summarized by comparison and analysis of computational results. The characteristics supply some academic foundations for design of supercritical elastic wing and improving aerodynamic characteristics of supercritical elastic wing.
出处
《国际航空航天科学》
2016年第3期68-74,共7页
Journal of Aerospace Science and Technology
基金
陕西省科技厅科学研究计划项目(2016JM1030)
陕西理工大学人才启动项目(SLGQD13(2)-21)联合资助。
