A new methodology has been developed for the automated optimal design of two-dimensional high-speed inlets. A semiempirical flow solver and an 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 flow condition, and secondly, 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 Applied Mechanics in Novosibirsk, Russia. The significant improvements of the total pressure recovery, achieved by the automated optimization loop, are verified using a full Navier-Stokes solver.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Fuel Technology
- Mechanical Engineering
- Space and Planetary Science