[akku]

Dear All,


I am using XFLR5 Version 6.09.01 Beta. I have been analyzing NACA 2206 for the following Reynolds Numbers viz, 75843, 151685, 227528, 303371, 379213, 455056, 530899, 606742 and 682584 for angle of attack in the range of -29 degrees to +29 degrees (in increments of 2 degrees). In my analysis, I am finding out that as I increase the number of panels required to generate the airfoil shape, I am getting lesser and lesser converged values of lift and drag coefficients (for different combinations of Reynolds number & angle of attack).


Of-course we know that higher number of panels are required to get a more accurate airfoil shape but in which case I am not getting sufficient number of converged values. What can be done ?. Where is the trade-off ?.


Thanks in Advance