Abstract：A transonic flutter model of a civil plane wing was investigated.The aerodynamic force in a flow field with fixed boundary was solved with N-S equations.The aerodynamic force in a flow field with moving boundary was solved with the simplified transonic small disturbance equations.The flutter characteristics were studied by combining the modal analysis results of structural dynamics and the aerodynamic force.The numerical simulations of flutter were finished before the model wind tunnel tests.Ater tests,the comparisons showed that the numerical results agree well with the test data; the calculated flutter frequencies are close to the those of test data; the flutter speed varies with Mach number,the flutter speed of the former and that of the latter have the same trend; the bottom positions of transonic pits measured and calculated agree well; the flutter speed difference between simulation and test is less than 10%,and less than 1% when Mach number is 0.60 or 0.70; the numerical method has a high accuracy,it can be used to predict wind tunnel tests’ results,and improve the reliability and the efficiency of wind tunnel tests; the method can also be a means of the compliance verification of civil aviation air worthness.
陈千一，窦忠谦，周铮，章俊杰. 机翼跨音速风洞颤振试验模型的计算分析[J]. 振动与冲击, 2017, 36(7): 99-103.
CHEN Qianyi,DOU Zhongqian,ZHOU Zheng,ZHANG Junjie. Numerical analysis of flutter test model in transonic wind tunnel of a wing. JOURNAL OF VIBRATION AND SHOCK, 2017, 36(7): 99-103.
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