BUG: Rotor source - corrected definition of Cl/Cd for series profile

src/fieldSources/basicSource/rotorDiskSource/profileModel/series/seriesProfile.C

@@ -2,7 +2,7 @@
   =========                 |
   \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox
    \\    /   O peration     |
-    \\  /    A nd           | Copyright (C) 2011 OpenFOAM Foundation
+    \\  /    A nd           | Copyright (C) 2011-2012 OpenFOAM Foundation
      \\/     M anipulation  |
 -------------------------------------------------------------------------------
 License
@@ -48,7 +48,7 @@ Foam::scalar Foam::seriesProfile::evaluate
 
     forAll(values, i)
     {
-        result += values[i]*cos((i+1)*xIn);
+        result += values[i]*sin((i + 1)*xIn);
     }
 
     return result;

src/fieldSources/basicSource/rotorDiskSource/profileModel/series/seriesProfile.H

@@ -2,7 +2,7 @@
   =========                 |
   \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox
    \\    /   O peration     |
-    \\  /    A nd           | Copyright (C) 2011 OpenFOAM Foundation
+    \\  /    A nd           | Copyright (C) 2011-2012 OpenFOAM Foundation
      \\/     M anipulation  |
 -------------------------------------------------------------------------------
 License
@@ -28,8 +28,8 @@ Description
     Series-up based profile data - drag and lift coefficients computed as
     sum of cosine series
 
-        Cd = sum_i(CdCoeff)*cos(i*AOA)
-        Cl = sum_i(ClCoeff)*cos(i*AOA)
+        Cd = sum_i(CdCoeff)*sin(i*AOA)
+        Cl = sum_i(ClCoeff)*sin(i*AOA)
 
     where:
         AOA = angle of attack [deg] converted to [rad] internally