76697588ed6da82c507a68074e63a30b809a8a99,trunk/SUAVE/Methods/Aerodynamics/Common/Fidelity_Zero/Lift/weissinger_vortex_lattice.py,,weissinger_vortex_lattice,#Any#Any#Any#,20

Before Change

        A_v = A*0.25/np.pi*T
        v   = np.sum(A_v,axis=1)
        
        Lfi = -T * (np.sin(twist_tc)-v)
        Lfk =  T * np.cos(twist_tc)   
        Lft = -Lfi*np.sin(twist_tc)+Lfk*np.cos(twist_tc)
        Dg  = Lfi*np.cos(twist_tc)+Lfk*np.sin(twist_tc)
            
        L  = deltax * Lft
        D  = deltax * Dg

After Change

    deltax = span/n
    
    sin_aoa = np.sin(aoa)
    cos_aoa = np.cos(aoa)

    if orientation == False :

        // discretizing the wing sections into panels            
        i              = np.arange(0,n)
        section_length = dchord/span*(span-(i+1)*deltax+deltax/2) + tip_chord
        twist_distri   = twist_rc + i/float(n)*(twist_tc-twist_rc)
        
        ya = np.atleast_2d((i)*deltax)
        yb = np.atleast_2d((i+1)*deltax)
        xa = np.atleast_2d(((i+1)*deltax-deltax/2)*np.tan(sweep) + 0.25*section_length)
        x  = np.atleast_2d(((i+1)*deltax-deltax/2)*np.tan(sweep) + 0.75*section_length)
        y  = np.atleast_2d(((i+1)*deltax-deltax/2))      
                
        RHS  = np.atleast_2d(np.sin(twist_distri+aoa))
        
        A = (whav(x,y,xa.T,ya.T)-whav(x,y,xa.T,yb.T)\
            -whav(x,y,xa.T,-ya.T)+whav(x,y,xa.T,-yb.T))*0.25/np.pi
    
        // Vortex strength computation by matrix inversion
        T = np.linalg.solve(A.T,RHS.T).T
        
        // Calculating the effective velocty         
        A_v = A*0.25/np.pi*T
        v   = np.sum(A_v,axis=1)
        
        Lfi = -T * (sin_aoa-v)
        Lfk =  T * cos_aoa 
        Lft = -Lfi * sin_aoa + Lfk * cos_aoa
        Dg  =  Lfi * cos_aoa + Lfk * sin_aoa
            
        L  = deltax * Lft
        D  = deltax * Dg

Instances