Aerodynamic shape optimization Nose Cone of F-35 Lightning II

Abstract

This project aims to maps out a potentially better design points for the Nose cone structure of the Lockheed Martin F-35 Lightning II aircraft. The optimization is performed by using the Built-In functions of MATLAB optimization. Computational Fluid Dynamics (CFD) analysis has conducted to predict the flow behavior mainly drag values around the particular shape of the nose cone. QUICKERSIM CFD software has been used to obtain the aerodynamics of the nose cone. Optimized shape is obtained at Mach 1.61 which is the certified max speed for the F-35 fighter jet. CFD solves the compressible Euler equations for the domain. The PARSEC curve approach has been applied for the physical two-dimensional shape of the nose. Two-dimensional shape of the nose seen from bird's eye view has selected for the obtain necessary simplicity for the projected deadline of the project and assumptions made accordingly. Optimization loop has been developed and implemented as to function automatically when the user initiated the main optimization. The necessary relation has been established inside of each script. Analysis has provided a solution close to nine percent decrease in drag values with out manipulating the constraints given.