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

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This commit is contained in:
andy
2012-04-16 11:11:49 +01:00
parent 477e38daef
commit faee006555
2 changed files with 5 additions and 5 deletions
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4
src/fieldSources/basicSource/rotorDiskSource/profileModel/series/seriesProfile.C
View File

@ -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;

6
src/fieldSources/basicSource/rotorDiskSource/profileModel/series/seriesProfile.H
View File

@ -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