计算力学学报2019，Vol.36Issue(1)：43-51,9.DOI:10.7511/jslx20170905004
高超声速舵面颤振的数值模拟影响因素研究
Study on influencing factors of the flutter numerical simulation of hypersonic control surface
摘要
Abstract
A numerical study of the flutter of a hypersonic control surface was presented based on the results of wind tunnel tests.Aerodynamic models and coupled iterative strategies were applied to predict the dynamic pressure for flutter.Four aerodynamic models were used including the third-order piston theory, the unified lifting surface theory, the Euler and the Navier-Stokes equations.The results indicated that all of the models led to similar and reasonable behaviour.The error between the numerical results and the experimental results was within 7％ for the first two models.The error was larger, more than 15％, when employing the time-domain loosely coupled method for the last two models.It was also discovered that a shock wave boundary-layer interaction induced by the model support structure was captured, which increased the flutter pressure to some extent, and the predicted results were closer to the experimental values after taking this influential factor into account.关键词
高超声速/颤振/风洞试验/计算流体力学/流固耦合Key words
hypersonic/flutter/wind tunnel test/computational fluid dynamics/fluid-solid coupling分类
数理科学引用本文复制引用
张兵,许辉,韩景龙,宣传伟..高超声速舵面颤振的数值模拟影响因素研究[J].计算力学学报,2019,36(1):43-51,9.基金项目
国家自然科学基金 (11302065) 资助项目. （11302065）
