Abstract: Plane-symmetric hypersonic vehicles suffer from high aerodynamic coupling, weak stability and strong nonlinearity problems during large-angle-of-attack maneuvering flight, which poses a challenge to aerodynamic characteristics research, control system design and ground validation. To meet the coupling characteristic evaluation requirement of next-generation hypersonic vehicle, an innovative virtual flight test system has been established for the first time in a 1m-scale high-speed wind tunnel. The system incorporates customized components such as a low-damping rig, a compact helm gear, and a high-performance control module. Utilizing the Bank-to-Turn control strategy, the test system has successfully simulated the vehicle's maneuvering flight under three control laws in the hypersonic wind tunnel. The test system offers a suitable solution for the coupling characteristics evaluation and control law validation, and provides a universal verification platform for aerodynamic design and flight control optimization.