6fd1cef5797fd76e8ea6b68ee9338dce759768ad,trunk/SUAVE/Methods/Aerodynamics/Common/Fidelity_Zero/Lift/compute_induced_velocity_matrix.py,,vortex,#Any#Any#Any#Any#Any#Any#Any#Any#Any#,172

Before Change

    R1R2Z  =  X_X1*Y_Y2 - Y_Y1*X_X2
    SQUARE = R1R2X*R1R2X + R1R2Y*R1R2Y + R1R2Z*R1R2Z
    SQUARE[SQUARE==0] = 1e-32
    R1     = np.sqrt(X_X1*X_X1 + Y_Y1*Y_Y1 + Z_Z1*Z_Z1) 
    R2     = np.sqrt(X_X2*X_X2 + Y_Y2*Y_Y2 + Z_Z2*Z_Z2) 
    R0R1   = X2_X1*X_X1 + Y2_Y1*Y_Y1 + Z2_Z1*Z_Z1
    R0R2   = X2_X1*X_X2 + Y2_Y1*Y_Y2 + Z2_Z1*Z_Z2
    RVEC   = np.array([R1R2X,R1R2Y,R1R2Z])
    COEF   = (1/(4*np.pi))*(RVEC/SQUARE) * (R0R1/R1 - R0R2/R2)

    if np.isnan(COEF).any():
        print("NaN!")       

    return COEF

def vortex_leg_from_A_to_inf(X,Y,Z,X1,Y1,Z1,tw): 

After Change

    R1R2X  = Y_Y1*Z_Z2 - Z_Z1*Y_Y2 
    R1R2Y  = Z_Z1*X_X2 - X_X1*Z_Z2
    R1R2Z  = X_X1*Y_Y2 - Y_Y1*X_X2
    SQUARE = np.square(R1R2X) + np.square(R1R2Y) + np.square(R1R2Z)
    SQUARE[SQUARE==0] = 1e-32
    R1     = np.sqrt(np.square(X_X1) + np.square(Y_Y1) + np.square(Z_Z1)) 
    R2     = np.sqrt(np.square(X_X2) + np.square(Y_Y2) + np.square(Z_Z2)) 
    R0R1   = X2_X1*X_X1 + Y2_Y1*Y_Y1 + Z2_Z1*Z_Z1

Instances