飞行器非定常气动力试验与建模研究

介绍了57°三角翼布局战斗机模型在CARDC直径3.2m风洞进行的俯仰、偏航和滚转3个方向大振幅振荡的非定常气动特性，试验的振幅为20°、35°，俯仰和偏航振荡的减缩频率为0～0.06，滚转振荡的减缩频率为0～0.2。另外利用基于频率域的Fourier变换法和非线性代数法，对非定常气动力建模进行了探讨，气动模型预测结果和试验结果具有较好的一致性。

An experimental investigation on unsteady aerodynamics and modeling for a fighter configuration

The experimental investigation conducted in CARDC-Dia. 3.2m subsonic wind tunnel for a fighter model with 57° delta wing are presented and the typical results are also discu.ssed in this paper. During the test forces and moments are measured under pitching, yawing and rolling oscillation with the amplitude of 20° ,35° and reduced frequency from 0 to 0.2 at various side slip and angles of attack for longitudinal and lateral motion respectively. On the basis of Fourier functional analysis and the linear aerodynamic theories, two aerodynamic models were built up. The calculated results with the models, the Fourier analysis model and the nonlinear model, show good agreement between different methods and test results.