Abstract: Strongly nonlinear coupling phenomenon between the aerodynamic parameters and the motion parameters are generally existed during the complex maneuvers for a modern high-performance flight vehicle, therefore the integrative wind tunnel test technique becomes essential for aerodynamics and flight dynamics. The technique of wind tunnel based virtual flight testing(WTBVFT) provides the capability to research those corresponding nonlinear couple problems between aerodynamic and motion parameters. The test model will experience freely all three degree-of-freedom rotational motion, the control surfaces can be real time controlled according to the flight control systems demands, while the aerodynamic loadings and motion parameters are measured simultaneously during the test. The WTBVFT tests the response and the control characters of the vehicle, achieves the aim of integrated research on the aerodynamics and the flight dynamics, and explores the aerodynamics/flight dynamics coupling mechanism. The technical issues, corresponding platform and verification tests of WTBVFT are introduced. The test results show that WTBVFT has the primarily experimental ability for integrated simulation of aerodynamics and flight dynamics for a missile mode.