Doublet Panel Method Help

[pcgamer549]

Hi,

I'm trying to predict the pressure distribution around a NACA 0010 foil using doublet distributions (using MATLAB). I can get the correct Cp prediction for a circle but when I transfer it to a airfoil shape I cannot get a correct Cp curve. I have tried modifying the Kutta Conditions to no avail. I have checked my doublet equations with a single plate and validated that my doublet equations are working correctly. I have looked in the Katz "Low Speed Aerdynamics" Book, but again to no success.

I have been debugging this for nearly 2 weeks and I no longer think I can be able to find the bug myself (I have a hunch that the mistake is simple, and I'm just overlooking it...).

I attached my code (at least I hope I did) to this post. Any help would be appreciated...Thanks!

 

[Illmatic1]

</code>The most important part of your code is the part which defines the doublet distributions. In order to get the correct pressure distribution around the NACA 0010 foil, you need to make sure that the doublet distribution is set up correctly. You should also check your boundary conditions and make sure that they are set up properly. Additionally, you should check the numerical methods you are using (e.g. finite difference, finite element, etc.) to ensure that they are converging correctly. If you have checked all these things and still cannot get the correct pressure distribution, then it is likely that you are either missing something subtle in your calculations or you are making a mistake in your code. In this case, it would be best to get help from someone who has experience with this kind of problem. Good luck!