Optimization of Aerodynamic Characteristics by Genetic Algorithm

Genetic algorithm optimization technique has been implemented for the aerofoil shape optimization. Normal to reference line method has been implemented for design space refinement. NACA 0012 symmetrical aerofoil was chosen as baseline aerofoil. Sequential computing technique has been applied. Composite wing models have been designed and fabricated for wind tunnel testing. Microcontroller has been designed and fabricated for varying the angle of attack of wing model in the wind tunnel. Aerodynamic characteristics of GA optimized wing models have been obtained first by experimental analysis from a subsonic, low Reynolds number wind tunnel at varying angle of attack and then by numerical second order vortex panel method. Modal analysis has been carried out by both experimental and finite element method. Bending and Torsional natural frequencies have been obtained. The aerodynamic characteristics and mode frequency results gleaned have been compared with standard NACA 2412 aerofoil. Computational time for Genetic Assisted Computational flow solver has been compared with Genetic Assisted Vortex panel method.