ComputeCoeffFromShape:

```------------------------------------------------------------------------
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)

------------------------------------------------------------------------
Form:
[cL, cD, cM] = ComputeCoeffFromShape( x, y,          n, alpha )
[cL, cD, cM] = ComputeCoeffFromShape(     imageFile, n, alpha )
[cL, cD, cM] = ComputeCoeffFromShape( 'airfoil.dat', n, alpha )
------------------------------------------------------------------------

------
Inputs
------
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)

-------
Outputs
-------
cL             (1,n) Lift coefficients
cD             (1,n) Drag coefficients
cM             (1,n) Moment coefficients

------------------------------------------------------------------------
References: Kuethe, A.M., and C. Chow, "Foundations of Aerodynamics,
Fifth Edition," John Wiley & Sons, 1998.
------------------------------------------------------------------------
```

Children:

```Common: Graphics/NewFig
Common: Graphics/Plot2D
Math: Analysis/FitPair
```