a068c94852f28630c7eeed3e66523fee665eb6e7,trunk/SUAVE/Plugins/OpenVSP/vsp_write.py,,write,#Any#Any#,20

Before Change

        origins   = turbofan.origin
        bpr       = turbofan.bypass_ratio
        
        if n_engines == 2:
            symmetric = 1
        else:
            symmetric = 0
            
        x = origins[0]
        y = origins[1]
        z = origins[2]
            

After Change

            
            // Calculate the local span
            if i_segs == n_segments:
                span_i = span*(1 - wing.Segments[i_segs-1].percent_span_location)/np.cos(dihedral_i*Units.deg)
            else:
                span_i = span*(wing.Segments[i_segs].percent_span_location-wing.Segments[i_segs-1].percent_span_location)/np.cos(dihedral_i*Units.deg)           
            
            // Insert the new wing section

Instances