Numerical simulation on aerodynamic characteristics of rocket with wraparound fins

Aiming at stability analysis for cone motion of rocket with wraparound fins, the flow field was numerically simulated. The accuracy of numerical simulation was verified by comparing computational and experimental results, and the side moment coefficient was obtained. The pressure contours on fin surface obtained during the experiment was used for analyzing the formation reasons of roll moment and side moment of rocket with wraparound fins. The roll damping moment coefficient was calculated by means of forced roll method and aerodynamic parameter identification technique, and the calculated results agree well with the experiment data. Finally unsteady flow filed of rocket with wraparound fins during the cone motion was numerically simulated, and it was found that the main effect of the cone motion on drag is the static effect caused by attack angle.