CST method is a powerful parameterization method because of its simplicity, robustness, and its ability to be generalized into various possible shapes of aerodynamic bodies. CST with low order polynomial is also suitable for airfoil preliminary design and optimization purpose since it only needs few parameters to give specific shape of airfoil. CST build the airfoil by summing the individual contribution of its basis function that is built by Bernstein Polynomial. The code is easy to use and also very easy to be modified for your own needs.
The input to CST_airfoil.m is the following:
- wl (lower surface weight)
- wu (upper surface weight)
- dz (trailing edge thickness)
- N (number of airfoil coordinates)
Where the output is a set of x and y coordinates of CST generated airfoil.
As a demonstration, you can try the following:
CST_airfoil([-1 -1 -1], [1 1 1],0,400)
or,
CST_airfoil([-0.1294 -0.0036 -0.0666], [0.206 0.2728 0.2292],0,400)
The latter will gives coordinates that resembles the shape of Clark-Y airfoil.
You can also easily add the order of CST by simply adding additional weight value on wl or wu inputs. For detail information you can refer to the original paper by Brenda Kulfan:
Kulfan, Brenda M. "A universal parametric geometry representation method—CST." AIAA Paper 62 (2007).
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