ComputeCoeffFromShape:
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Computes lift, drag and moment coefficients for an airfoil.
The airfoil may be entered as a file with x and y coordinates
an image file (such as a .jpg) or as data.
Files of numbers are a text file with a .dat suffix and consist
of a line with a name and then a list of x,y pairs.
Type
ComputeCoeffFromShape
for a demo. It will demonstrate an airfoil from a .jpg file and
and airfoil from a .dat file.
The computation uses the vortex panel method and is for inviscid
flow only.
n can be a number of panels (top and bottom) or a list of
x-coordinates for both top and bottom.
If you enter x and y, x must form a closed loop (i.e. start and end
at 1.0)
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Form:
[cL, cD, cM] = ComputeCoeffFromShape( x, y, n, alpha )
[cL, cD, cM] = ComputeCoeffFromShape( imageFile, n, alpha )
[cL, cD, cM] = ComputeCoeffFromShape( 'airfoil.dat', n, alpha )
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Inputs
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x (1,:) x coordinates or file name
y or n (1,:) y coordinates or number of panels or alpha
n (1,1) Number of panels or alpha (deg)
alpha (1,n) Angles of attack (deg)
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Outputs
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cL (1,n) Lift coefficients
cD (1,n) Drag coefficients
cM (1,n) Moment coefficients
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References: Kuethe, A.M., and C. Chow, "Foundations of Aerodynamics,
Fifth Edition," John Wiley & Sons, 1998.
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Children:
Common: Graphics/NewFig
Common: Graphics/Plot2D
Math: Analysis/FitPair