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: airfoilMicroTabDeltaCoeff.m
    path of file: ./repos/LADAC/aerodynamics/airfoil/micro_tab
    
    the code of the file until where you have to start completion: function [Delta_c_L,Delta_c_D,Delta_c_m] = airfoilMicroTabDeltaCoeff( ...
    micro_tab, circulation, state )
% airfoilMicroTabDeltaCoeff compute the Delta lift, drag and moment
% coefficient for a micro-tab [1]
% 
% Inputs:
%   micro_tab           micro-tab struct (see airfoilMicroTabCreate)
%   circulation         circulation struct (see wingSetCirculationUnsteady)
%   state               state of the micro-tab (1xN array for N tabs;
%                       the arrays inside circulation must also have N
%                       elements)
% 

    
function [Delta_c_L,Delta_c_D,Delta_c_m] = airfoilMicroTabDeltaCoeff( ...
    micro_tab, circulation, state )
% airfoilMicroTabDeltaCoeff compute the Delta lift, drag and moment
% coefficient for a micro-tab [1]
% 
% Inputs:
%   micro_tab           micro-tab struct (see airfoilMicroTabCreate)
%   circulation         circulation struct (see wingSetCirculationUnsteady)
%   state               state of the micro-tab (1xN array for N tabs;
%                       the arrays inside circulation must also have N
%                       elements)
% 
% Outputs:
%   Delta_c_L           Delta lift coefficient (1xN array)
%   Delta_c_D           Delta drag coefficient (1xN array)
%   Delta_c_m           Delta pitching moment coefficient (1xN array)
% 
% See also:
%   airfoilMicroTabLoadParams, airfoilMicroTabStateDeriv
% 
% Literature:
%   [1] Khalil, K., Asaro, S., & Bauknecht, A. (2021). Active flow control
%       devices for wing load alleviation. Journal of Aircraft, 1-17.
%       https://arc.aiaa.org/doi/pdf/10.2514/1.C036426?casa_token=ev6VDwEIkCIAAAAA:4g1h23YzMzEHPzJskme5LC45Gs0FkqwqlveAhscZVpJXFK0Do3Mh9TEMuuIvwbp9SPNOZkFzlA
% 

% Disclamer:
%   SPDX-License-Identifier: GPL-3.0-only
% 
%   Copyright (C) 2020-2022 Yannic Beyer
%   Copyright (C) 2022 TU Braunschweig, Institute of Flight Guidance
% *************************************************************************

fdcl = airfoilAnalytic0515Ma( micro_tab.net.wcl, circulation.Ma );
fdcd = airfoilAnalytic0515Ma( micro_tab.net.wcd, circulation.Ma );
fdcm = airfoilAnalytic0515Ma( micro_tab.net.wcm, circulation.Ma );
Delta_c_L = airfoilAnalytic0515De( fdcl, [circulation.alpha_eff;state] );
Delta_c_D = airfoilAnalytic0515De( fdcd, [circulation.alpha_eff;state] );
Delta_c_m = airfoilAnalytic0515De( fdcm, [circulation.alpha_eff;state] );
    
end