针对某高超声速舵面颤振风洞试验模型开展了数值模拟研究,采用多种气动力模型和耦合迭代策略,研究对颤振预测结果的影响.计算结果表明,采用三阶活塞理论、统一升力面理论、Euler方程和N-S方程的颤振动压预测结果较接近,与试验值误差均在7％以内.采用时域方法计算时,松耦合方法的误差较大,超过15％.同时还发现,支撑机构会带来激波边界层干扰效应,一定程度上提高了颤振动压,考虑该因素的预测结果与试验值更接近.%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.
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