[twolfe13]

I have an in-house code written in MATLAB that requires a blade thickness distribution file (x,y tab delimited text format). I want to specify inlet and outlet blade angles (beta1 & beta2) which will distort the blade and generate a camber line. My question is two-part:

1) How should the camber line be generated from inlet and outlet blade angles? I have a few methods in mind, but I'm having trouble finding a general accepted method. Spline? Polynomial? Etc.

2) Once this camber line is generated, how do I modify the blade thickness distribution of a common (NACA 6 series) airfoil to generate a new blade thickness distribution?

I originally thought that the blade thickness distribution would not need to be modified since it's measured perpendicular to the camber line anyway, but that results in a very ugly airfoil (kind of diamond-shaped with a tear drop profile at the LE & TE).

The problem is that the code is embedded in an executable that I do not have the source code for, so I can't actually see what's going on inside the black box to try to reverse engineer this.

[apoorv]

Hi,

There are many common meanline for turbomachinery blades : Circular arc, Quadratic, Cubic, Parabolic and now a days NURBS/Bezier curve based meanline.

Similarly there are many thickness distribution equations; but NACA distribution is not much preferred now a days. Other few are multiple circular arc distribution, British C-series distribution. Now a days Nurbs distribution is also common.

I have few text input driven fortran based 2d/q3d/3d direct design code for my own use. If you need 2d version, may be I can help. Please drop me a personal message.

Best Regards

Apoorv