Abstract: Wind tunnel virtual flight technique (VFT) can be used to verify and evaluate the flight control system of an aircraft. The flight control subsystem, core of VFT, employs rapid control system prototyping to achieve auto generation and rapid implementation of embedded real-time flight control codes, reduce the difficulty of flight control system integration, and enhance wind tunnel virtual flight test efficiency. This paper summarizes the system component and state of arts of Φ3.2m wind tunnel virtual flight system, introduces the rapid prototyping development platform and implementation methods of the flight control system based on that system. Commonality and openness of the system was verified through full digital simulation, semi-physical simulation and wind tunnel virtual flight tests on a scale aircraft model. This technique can fulfill the requirements of control system integration for various aircraft wind tunnel virtual flight tests.