function [CH,CQ]=RotorCHQ(T,alpha,V,Omega,rho,rotor) %ROTORCHQ % [CH,CQ]=RotorCHQ(T,alpha,V,Omega,rho,rotor) % Returns rotor drag and torque coefficients CH and CQ % the subsequent drag is calculated from % H = rho*A*(Omega*rotor.R)^2*CH(T,alpha,V,Omega,rho,rotor) % and torque from % Q = rho*A*Omega^2*rotor.R^3*CQ(T,alpha,V,Omega,rho,rotor) % % CH: rotor drag coefficient % CQ: rotor torque coefficient % % T: rotor thrust % 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 AircraftCoefficients.m) % (c) James Whidborne % Cranfield University, 27 February 2019 [~,CH,CQ]=RotorC(T,alpha,V,Omega,rho,rotor); % Returns rotor thrust coefficient end