Numerical aero-thermal-structural analyses of a fighter jet wing during supersonic flights

Current research paper deals with the numerical analysis of an idealized fighter jet wing in a multi-module aero-thermal-structural environment during supersonic flights. At high Mach number, heat is generated due to the friction between the body and the fluid flow, which must be considered for structural analyses. Six different Mach numbers ranging from 1.25 to 2.5 are chosen to understand the effect of viscous heating on the wing model. Ansys CFD is coupled with thermal/structural module to calculate the numerical results. It is observed that for Mach number 1.75 and beyond, equivalent Von-mises stress due to pressure load is almost identical. However, with viscous heating consideration, equivalent stress values are increased with higher Mach number which magnifies the significance of thermal loading on the structure