NACA method for calculus of pressure coefficent distribution

With this script you can calculate a pressure coefficent distribution around any profile of the four digit NACA series

With this script you can calculate a pressure coefficent distribution around any profile of the four digit NACA series.

1) V_v is the ratio velocity for symmetric airfoil at 0° AOA

2) Delta_va_V is the distribution of velocity for symmetric airfoli

3) Delta_v_V is the distribution of velocity for mean line at Cl_i and AOA_i (where i = ideal)

4) f_alpha is a correction factor caculate as difference between desiderate C_l and Cl_i , considering a Cl_0 = 1 relative at the AOA_i