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| Study on influencing factors of the flutter numerical simulation of hypersonic control surface |
| Received:September 05, 2017 Revised:December 19, 2017 |
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| DOI：10.7511/jslx20170905004 |
| KeyWord:hypersonic flutter wind tunnel test computational fluid dynamics fluid-solid coupling |
| Author | Institution |
| 张兵 |
合肥工业大学 机械工程学院, 合肥 |
| 许辉 |
合肥工业大学 机械工程学院, 合肥 |
| 韩景龙 |
南京航空航天大学 航空宇航学院, 南京 |
| 宣传伟 |
南京航空航天大学 航空宇航学院, 南京 |
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| 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. |
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