You are an expert in writing code in many different languages. Your goal is to perform code completion for the following code, keeping in mind the rest of the code and the file meta data.
    Metadata details:
    filename: wingSetCirculationDlm.m
    path of file: ./repos/LADAC/aerodynamics/vlm_wing/state/aero
    
    the code of the file until where you have to start completion: function wing = wingSetCirculationDlm( wing ) %#codegen
% wingSetCirculationDlm sets the wing.state.aero.circulation struct in
% a wing struct.
%   The circulation parameters for a wing with spanwise discretization are
%   computed. Therefore, unsteady airfoil aerodynamics can be considered.
% 
% Inputs:
% 	wing           	wing struct, see wingCreate
% 
% Outputs:
% 	wing           	wing struct, see wingCreate

% Disclamer:
%   SPDX-License-Identifier: GPL-2.0-only
% 
%   Copyright (C) 2022 Yannic Beyer
%   Copyright (C) 2022 TU Braunschweig, Institute of Flight Guidance
% *************************************************************************


abs_V_i = zeros( 1, wing.n_panel );


    
function wing = wingSetCirculationDlm( wing ) %#codegen
% wingSetCirculationDlm sets the wing.state.aero.circulation struct in
% a wing struct.
%   The circulation parameters for a wing with spanwise discretization are
%   computed. Therefore, unsteady airfoil aerodynamics can be considered.
% 
% Inputs:
% 	wing           	wing struct, see wingCreate
% 
% Outputs:
% 	wing           	wing struct, see wingCreate

% Disclamer:
%   SPDX-License-Identifier: GPL-2.0-only
% 
%   Copyright (C) 2022 Yannic Beyer
%   Copyright (C) 2022 TU Braunschweig, Institute of Flight Guidance
% *************************************************************************


abs_V_i = zeros( 1, wing.n_panel );

% compute u_n ([5], nomenclatrue, Fig. 3) in aircraft frame
u_n = wingGetNormalVectorFromGeometry( wing.state.geometry );

% [katz & Plotkin, tau_i in eq. (13.149)]
tau_i = diff(wing.geometry.vortex.pos(:,1:end