Aerodynamic heating of an inflatable reentry vehicle, TITANS, which is one of the innovative reentry technologies, was investigated using a tightly coupled approach involving computational fluid dynamics and structure analysis. A strong shock wave at the front and a wake structure behind the TITANS vehicle were clarified. It was indicated that thermochemically nonequilibrium flow appears for a case of the peak heating altitude in the trajectory of mission. A heat flux distribution due to high temperature gradient near deformed surface was uncovered. The heat flux at the capsule part of the TITANS vehicle increased, while that on the membrane decreases. This is because the shock wave formation changed by the membrane deformation. In addition, it was indicated that wrinkles on the membrane formed by the deformation causes increase in heat flux.