diff --git a/src/configs/caradonna1981.m b/src/configs/caradonna1981.m index 8c49f3bd053066f99b8a21c3122529cba1db1c2b..cdc0bd49fe08a7f0bfe36e0c54669eb7f274d452 100644 --- a/src/configs/caradonna1981.m +++ b/src/configs/caradonna1981.m @@ -94,7 +94,7 @@ Airfoil.polarType = 'file'; % Type of polar to use ('file', 'polynomial') Airfoil.coordFile = 'airfoil_data/naca0012.dat'; % If Airfoil.polarType == 'file' -Airfoil.polarFile = 'airfoil_data/NACA_0012-Re_2e5-1e7.mat'; +Airfoil.polarFile = 'airfoil_data/NACA_0012-Re_1e5-1e7.mat'; Airfoil.extrapMethod = 'viterna'; % Polar extrapol. ('none', 'spline', 'Viterna') % ================================================================================================== diff --git a/src/solvers/indvel.m b/src/solvers/indvel.m index b7d04237f0a7b8e7a8c2c69f7c2936cf5b86f939..98e53ffe61ae3bfc970b84e725567bac9d73c171 100644 --- a/src/solvers/indvel.m +++ b/src/solvers/indvel.m @@ -89,8 +89,8 @@ function indvel(OpRot, Mod) dD = coeff2force(cd, OpRot, relVel); % Thrust and torque contributions - dFa = dL .* cos(phi) - dD .* sin(phi); - dFu = dL .* sin(phi) + dD .* cos(phi); + dFa = OpRot.Rot.nBlades * (dL .* cos(phi) - dD .* sin(phi)); + dFu = OpRot.Rot.nBlades * (dL .* sin(phi) + dD .* cos(phi)); % Final system to solve for v and u vw = OpRot.Op.speed + dFa ./ dmdot ./ K_T; @@ -125,7 +125,7 @@ function force = coeff2force(coeff, OpRot, speed) % COEFF2FORCE Convert aerodynamic coefficient to force rho = OpRot.Op.Flow.rho; - nondim = OpRot.Rot.nBlades .* (0.5 * rho * OpRot.Rot.Bl.area .* speed.^2); + nondim = 0.5 * rho * 2 * pi * OpRot.Rot.Bl.area .* speed.^2; force = coeff .* nondim;