AUTOMATED OPTIMAL-DESIGN OF 2-DIMENSIONAL SUPERSONIC MISSILE INLETS

A new methodology has been developed for the automated optimal design of two-dimensional highspeed inlets. A semiempirical flow solver and a n improved genetic algorithm are linked within an automated loop. The purpose of this process is to maximize the total pressure recovery of the missile inlet: first of all, for one upstream now condition, and s econdly, for an entire mission. This innovative design strategy allows great improvement of the original inlet design in a very short period of time. Successful results are presented for optimizations of inlets originally designed and tested at the Institute of Theoretical and Ap plied Mechanics in Novosibirsk, Russia. The significant improvements o f the total pressure recovery, achieved by the automated optimization Loop, are verified using a full Navier-Stokes solver.