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

     data_len = len(data_block)
     xfoil_aoa= np.zeros(data_len)
     xfoil_cl = np.zeros(data_len)
     xfoil_cd = np.zeros(data_len)     
     
     // Loop through each value: append to each column
     for line_count , line in enumerate(data_block):

Instances