function [CQ]=RotorCQ(T,alpha,V,Omega,rho,rotor) %ROTORCQ % [CQ]=RotorCQ(T,alpha,V,Omega,rho,rotor) % Returns rotor blade torque coefficient CQ(T) % the subsequent blade torque is calculated from % Q = ? A ?^2 R^3 CQ(T,alphar,V,Omega,rho,rotor) % % CQ: rotor drag coefficient % % T: rotor thrust (N) % alpha : angle of attack/wind incidence angle (rad) % V : incident windspeed (m/s) % Omega : rotor speed (rad/sec) % rho: air density (kg/m^3) % rotor: vehicle rotor coefficients structure (see Coefficients.m) % (c) James Whidborne % Cranfield University, 19 August 2020 [~,~,CQ]=RotorC(T,alpha,V,Omega,rho,rotor); % Returns rotor blade torque coefficient end