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| Influence of flow disturb on Transonic Flutter Characteristic of Aircraft T-Tail |
| LIANG Ji1 YANG Fei1 YANG Zhi-chun2 |
| 1.Stress Department, Shanghai Aircraft Design And Research Institute of COMAC, Shanghai, 200232, China2. School of Aeronautics, Northwestern Polytechnical University, Xi’an, 710072 |
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Abstract This research investigates the effect of flow disturb on transonic flutter characteristic of aircraft T-tail. The tradition transonic wind tunnel flutter test is conducted in non-flow disturb wind tunnel. And the influence of flow disturb on flutter isn’t considered in transonic flutter wind tunnel test. A body installation is used to simulate flow disturb in transonic wind tunnel. Results obtained for non-flow disturb and flow disturb are compared and discussed in detail. The flutter coupled mode is changed from H-tail bending/torsion mode of non-flow disturb to V-tail bending/torsion mode of flow disturb. In addition, the flutter dynamic pressures for aircraft T-tail become much lower when the flow disturb is functioned. The out wing flow disturb is more critical than the in-plane wing flow disturb. The result analysis is shown that the shock wave from transonic flow disturb influenced on V-tail unsteady aerodynamic force, once the damping is decreased to its critical flutter damping that the V-tail flutter would occurred early than H-tail flutter, at the same time the H-tail flutter damping is enough high, then the flutter coupled mode is changed and the flutter dynamic pressures is decreased for T-tail. The flow disturb should be analyzed in flutter model wind tunnel test if the test results is different from the prediction .
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Received: 23 June 2011
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2013, Vol. 32 
