Wind Tunnel Test and CFD Numerical Simulation of Dynamic Derivative for a Certain Type of Missile

Abstract

The accurate prediction of dynamic derivative is of significant importance for the successful development of missile weapons. Taking the dynamic performance of a certain missile as research subject, the free vibration method is used in FD06 wind tunnel to accomplish the dynamic performance experiment, and get the typical decay curves of amplitude and dynamic derivatives in pitching and rolling directions. On the basis of dual time-stepping approach, the unsteady N-S equation and forced movement equation are solved by numerical value, which can obtain the pitching and rolling dynamic derivatives of the missile. The results show that the CFD numerical simulation results are in accordance with wind-tunnel test data, which can provide a reference for the following engineering model development in a certain range of Mach numbers and angles of attack.

Keywords

• dynamic stability
• pitch damping derivative
• roll damping derivative
• wind tunnel test
• cfd nume-rical simulation