Abstract: Wind tunnel test is one of the most important methods to obtain the dynamic derivatives. A test system for the high-speed wind tunnel was developed to simulate the actual flight motion of projectile/rocket in the wind tunnel and improve the measuring level of dynamic derivatives. The system includes a control subsystem, a data acquisition subsystem, a data processing subsystem, and three different test devices, i.e., small and medium slenderness ratio model test device, large slenderness model pitch oscillation test device and spinning projectile model test device. For the small and medium slenderness ratio (L/d＜15) models, the traditional forced vibration method is used to establish the roll, yaw and pitch oscillation test devices. For the small caliber and large slenderness ratio (L/d≥15) model, the tail-forced vibration method is adopted for test device. For two-degrees-of-freedom spinning projectile model, a motor is used as driven device. The entire system was validated through wind tunnel test with standard model. The results show that the measured results of the small and medium slenderness ratio models obtained at different Mach numbers and angles of attack have high accuracy. Compared with domestic and foreign experimental data and CFD data, the experimental results here are within acceptable error range. The dynamic derivative test devices for large slenderness ratio and spinning projectile models have high engineering application value.

Key words: projectile/rocketmodel, dynamicderivative, testsystem, high-speedwindtunnel, BasicFinnermodel