Computational Fluid Dynamics Analysis of an Optimized Load-Distribution Propeller

B = number of propeller blades CD = drag coefficient CL = lift coefficient CP = power coefficient, P= n D CT = thrust coefficient, T= n D c = chord D = propeller diameter G = normalized circulation function GG = Goldstein’s normalized circulation function GP = Prandtl’s normalized circulation function J = advance ratio, v0=nD M = Mach number n = propeller revolutions per second, =2 P = power Q = torque R = propeller radius Re = Reynolds number RH = propeller hub radius R1 = wake radius r = radial coordinate S = propeller disk area, R T = thrust ua = axial induced velocity u = angular induced velocity v = resultant velocity v0 = advance velocity w = axial vortex displacement velocity y = nondimensional wall distance = angle of attack = blade pitch angle = circulation = drag-to-lift ratio = propeller efficiency = propeller blade pitch, v0t0 2 v0= 1 = wake pitch = speed ratio, v0= R 1 = wake speed ratio, v0 w = R1 = nondimensional radius, r=R 1 = nondimensional wake radius, r=R1 = fluid density = flow angle = propeller angular velocity