Numerical aerodynamic-thermal-structural analyses of missile fin configuration during supersonic flight conditions

Attention in this work is focused on aerodynamic heating and aero-thermo-mechanical analysis of fin type structures on the missile at supersonic flight. At high Mach number the heat due to friction between body and flow, i.e. viscous heating must be taken into account because the velocity field is coupled with the temperature field. The flow field around the fins of the missile and especially the temperature distribution on its surface, as well as aerodynamic-thermal-structural analyses are numerically modeled in ANSYS Workbench environment. The investigation was carried out for two Mach numbers (M = 2.3 and M = 3.7). Own available structural experimental results have been used for computational structural mechanics (CSM) validation and verification, in order to assure credibility of numerical fluid-thermal-structure interaction (FTSI). Conducted simulations were carried out to better understand the FTSIs of the missile fin during supersonic flight