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: simpleWingGetPitchDamping.m
    path of file: ./repos/LADAC/aerodynamics/simple_wing
    
    the code of the file until where you have to start completion: function C_m_damp = simpleWingGetPitchDamping( wing, q_Aw, V_A ) %#codegen
% pitchDamping computes the pitching moment coefficient due to a pitch
% rate.
% 
% Inputs:
%   wing            simple wing struct (see loadSimpleWingParams)
%   q_Ab            pitching rate in wing frame, in rad/s
%   V_A             airspeed, in m/s
% 
% Outputs:
%   C_m_damp        pitching moment coefficient due to a pitch rate

    
function C_m_damp = simpleWingGetPitchDamping( wing, q_Aw, V_A ) %#codegen
% pitchDamping computes the pitching moment coefficient due to a pitch
% rate.
% 
% Inputs:
%   wing            simple wing struct (see loadSimpleWingParams)
%   q_Ab            pitching rate in wing frame, in rad/s
%   V_A             airspeed, in m/s
% 
% Outputs:
%   C_m_damp        pitching moment coefficient due to a pitch rate
% 
% Literature:
%   [1] Schlichting, H. & Truckenbrodt, E. (2001): Aerodynamik des
%       Flugzeuges - Teil 2, Springer.
% 

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

C_m_dOmega = wing.C_m_dOmega_0;
c = wing.geometry.c;

% compute dimensionless pitching rate according to [1, p. 91]
Omega_y = q_Aw * c / max( V_A, 0.001 );

C_m_damp = C_m_dOmega * Omega_y;

end