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Unsteady transonic aerodynamics during wing flutter

机译：机翼颤振过程中不稳定的跨音速空气动力学

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摘要

Unsteady pressure distributions of a two-dimensional super-critical wing while it was fluttering were measured in the transonic flow regime. The results were compared with those by the Navier-Stokes code which includes wind-tunnel wall effects. Although there were discrepancies between the experimental results and the analytical model for the pressure phase delay distribution, no disagreements were observed for the pitching first harmonics provided that there was no large flow separation. In the tests, the flutter was forced to be suppressed soon after its onset before it reached a limit cycle oscillation (LCO) where the amplitude of the pitching angle was supposed to be over 2 degrees.
机译：在跨音速流态下，测量了二维超临界机翼在颤动时的非定常压力分布。将结果与包含风洞墙效应的Navier-Stokes代码进行了比较。尽管压力相位延迟分布的实验结果与分析模型之间存在差异，但前提是在没有大的流动分离的情况下，对于俯仰一次谐波没有观察到分歧。在测试中，颤振在发作后不久就被迫抑制，直到达到极限周期振荡（LCO），此时俯仰角的振幅应该超过2度。

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