Implementation of the Numerical Optimization for the Micro-Air Vehicle Propeller

Abstract

An algorithm used for the optimization of the design of the MAV(Micro-Air vehicle) propeller has been presented. Also, as a result of the adopted optimization process, a detailed description of the design concept of the MAV propeller is presented. The design procedure involves three steps. First, the airfoil shape is optimized to provide the maximum lift-to-drag ratio in each section. Here, for the calculation of the aerodynamic coefficients, Xfoil code has been used. Second, the blade shape is optimized, using the minimum energy loss method under given design conditions. Finally, the optimal value for the propeller efficiency has been selected from the calculated performances corresponding to given geometries and operating conditions, using the response surface method. The feasibility of the design space is checked as the probability of success obtained from response surface methodology and Monte Carlo simulation. And using Chebyshev inequality, the design space is moved to high feasible region. It is taken the loiter velocity for a single design point, design variables considered are the blade diameter and the motor rpm which constitute an advance ratio and the supplied power. The imposed constraints are the ranges of the required thrust, the activity factor and the Mach number. The performance of the optimized propeller has been compared with that of the Black Widow propeller for the standard design condition, and thereby the presented algorithm has been validated.