Aerodynamic-Shape Optimization of Supersonic-Missiles Using Monte-Carlo

摘要

This paper presents a fast and reliable technique for aerodynamic shape optimization of supersonic missiles using Monte Carlo optimization method. The technique is based on two modules: Aerodynamics module and optimization module. The aerodynamic module is based on components build-up method where analytical, and semi-empirical of different missile components were added together, with some interference factors, to calculate the overall aerodynamics of the missile. The Aerodynamics module is validated against known wind tunnel data and showed good agreement. The optimization module is aimed at finding Missile geometry (such as length, fins dimensions and fins location, etc.) which maximize lift-over-drag using Monte Carlo technique. Monte Carlo simulation Technique has proved itself as a simple and easy to implement tool for aerospace vehicles shape optimization.