Continuous varying dynamic pressure wind tunnel test method and numerical calculation of flutter characteristics of horizontal tail model
LIU Nan1,2, YI Jianing1,2, WANG Dong1,2, HOU Liangxue1,2, YANG Ximing1,2
1. AVIC Aerodynamic Research Institute, Shenyang 110034, China;
2. Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Research, Shenyang 110034, China
Abstract：In order to improve efficiency and safety of transonic flutter tests in a temporary impulse wind tunnel, an efficient flutter prediction method was established based on the auto-regressive moving average (ARMA) system identification method. Based on compensation decoupling and expert PID, a constant Mach number continuous variable pressure flow field control technology was developed for the FL-60 wind tunnel. Firstly, the ARMA system identification method was verified with the international standard model AGARD445.6 wing, and it was shown that the difference between the calculation results for flutter velocity pressure and frequency and those with the CFD/CSD coupled method is not more than 4%. Then, the flow field of the FL-60 wind tunnel was debugged to verify the continuous variable pressure flow field control of the FL-60 wind tunnel, and it was shown that velocity pressure variation has high linearity and the control accuracy of Mach number is ± 0.003. Finally, flutter tests of the flat tail model with continuous varying velocity pressure were conducted, and the results showed that the difference between flutter velocity pressures obtained by step tests and continuous varying velocity pressure tests is less than 2%; the flutter boundary calculation results agree well with those of wind tunnel tests; the proposed numerical method can provide a good guidance for test arrangement before test.
刘南，易家宁，王冬，侯良学，杨希明. 平尾模型连续变速压颤振试验方法及数值计算研究[J]. 振动与冲击, 2021, 40(15): 11-17.
LIU Nan, YI Jianing, WANG Dong, HOU Liangxue, YANG Ximing. Continuous varying dynamic pressure wind tunnel test method and numerical calculation of flutter characteristics of horizontal tail model. JOURNAL OF VIBRATION AND SHOCK, 2021, 40(15): 11-17.
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