Prediction of Aerodynamic Coefficients and Analysis of Flow Past a Supersonic Missile

摘要

This study is focused on application of CFD to evaluate the aerodynamic coefficients of tail controlled tactical missile configuration. Coefficients of lift, drag and pitching moment are calculated for a missile configuration and analyzed for supersonic speeds of Mach 2, 3 and 4 with angles of attack varying from -20o to +20o. Shock-wave formation, velocity and thermal boundary layers along with other qualitative aspects of flow field around the missile configuration are presented in detail. Missile DATCOM is also employed for calculation of aerodynamic coefficients for the same missile configuration. The comparative study of the two prediction techniques is presented. CFD post processing tools were employed to visualize the flow field around a supersonic missile under study. This research work can serve as a reference for aerodynamicists to evaluate the aerodynamic characteristics of similar designs.