HOU Liangxue12， ZHANG Ge12， LIU Nan12，WANG Dong12，QIAN Wei3，YANG Ximing12
1. Aerodynamic Research Institute, AVIC, Shenyang 110034, China;
2. Aeronautic Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Research, Shenyang 110034, China;
3. School of Aeronautics and Astronautics, Dalian University of Technology, Dalian 116024, China
Abstract：Aircraft’s flutter boundary fast dropping under transonic working condition is one of important states for structure design and strength checking. At present, the transonic flutter boundary can’t be correctly predicted using the linear analysis technique based on the di-pole grid method. Wind tunnel test is still an important means to study aircraft’s transonic flutter characteristics. Here, two sets of flutter test standard models were taken as the study objects to conduct wind tunnel transonic tests in the FL-3 wind tunnel. The PEAK-HOLD subcritical response analysis method was used to predict models’ transonic flutter boundary. Furthermore, the ZAERO numerical computation method and the CFD/CSD coupled one were used to predict models’ flutter boundary, respectively. The results showed that the flutter boundary predicted with the PEAK-HOLD method has a better tendency and it is reasonable and reliable; the prediction accuracy of the transonic flutter boundary using the ZAERO linear method is lower, but the transonic flutter boundary predicted using the CFD/CSD coupled nonlinear method agrees better with that using wind tunnel tests to verify the reliability of wind tunnel tests and numerical computation.
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