Design optimization of a rocket engine’s inner liner with improved response surface methodology

This article presents the optimization of design a subscale effusion-cooled rocket engine inner liner made porous composite material, with aim improving ability coolant film to protect combustion chamber wall from thermochemical attacks. The problem is defined as global minimization and solved using response surface methodology (RSM). Recommendations construct an efficient D-optimal in constrained domain experiments theory are provided. Computational fluid dynamics simulations carried out provide measurements response. iteratively reweighted least squares method used fit regression models improve efficiency RSM no additional cost. Enhanced properties for optimal show that was properly successfully optimized. These results demonstrate method.