I haven't done a lot of work with XFOIL for 3D airfoils, and as far as I know it can only handle 2D profiles. Like I said, though, I'm not sure. For my 3D model, I am capturing CL/CD as a function of both angular position and height of the blade. The local Reynolds numbers are different as you move across the blade, so finding CL/CD for each "blade element" basically translates to "plugging in the correct alfa and Re". Other than that, the logic sounds good.
What I want to do is this:
1. Choose six or seven standard profiles at specific lengths across the blade.
2. Calculate the Cd and Cl for the design Tip speed ratio (or design windspeed) for the entire blade. This should involve:
- Calculating Cd and Cl for each Blade Element at design wind speed using XFOIL.
- Integrating over the blade (is this correct?).
3. Calculate Cd and Cl over a range of windspeeds for the entire blade (perhaps an iteration of steps in two above).
4. Introduce an additional blade angle of twist to make the blade stall in higher speeds, and re-calculate the Cd, Cl for the above. This will have the effect of changing the Angle of Attack across the blade.
First of all, it's
I think your script is a good starting point, however, I'm completely new to XFOIL, python, matlab, and pearl. (New as in, haven't even run Hello World yet). I'm pretty sure I can adopt your matlab code to python though.
I'm confused on a few things:
1. Does the above list seem to miss anything?
2. I don't understand the XFOIL interface... help here is very much appreciated.
3. Using your scripts produce a bunch of files. How do I find the Cd and Cl of my profile under the conditions specified?
Thanks so much!