Abstract: 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.