摘要
The flutter characteristics of a airfoil with two degree of freedom was studied, in which the structural parameters were considered as linear. The N-S equations as governing equations were used to calculate the nonlinear unsteady aerodynamics at transonic speed. The flutter motion equations in combination with N-S equations were solved by time advancing method to calculate the structured response. An implicit lower-upper-factorized algorithm in a body-fitted coordinate system was constructed, in which a simple upwind scheme was adopted. Simulation results for NACA64A006 airfoil show that variation of flutter critical velocity with Mach number is given and the nonlinear nature of flutter phenomenon appears clearly.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 341-344 |
| 页数 | 4 |
| 期刊 | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| 卷 | 19 |
| 期 | 3 |
| 出版状态 | 已出版 - 8月 2001 |