5678e66aaa00587902c71449bf87270e9d07384f,trunk/SUAVE/Methods/Aerodynamics/XFOIL/compute_airfoil_polars.py,,read_airfoil_polars,#Any#,35

Before Change

       
    
     num_airfoils = len(airfoil)
     xfoil_polars = Data()
     xfoil_polars.aoa= np.zeros((num_airfoils,220))
     xfoil_polars.cl = np.zeros((num_airfoils,220))
     xfoil_polars.cd = np.zeros((num_airfoils,220))
     

After Change

          xfoil_cl[line_count]  = float(data_block[line_count][10:17].strip())
          xfoil_cd[line_count]  = float(data_block[line_count][20:27].strip())  
               
     return xfoil_cl , xfoil_cd , xfoil_aoa

Instances