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: getWetWing.m
    path of file: ./repos/LADAC-Examples/common_functions
    
    the code of the file until where you have to start completion: function wing_wet = getWetWing( tailsitter )

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

wing_dry = tailsitter.aero.wing;

wing_wet = wing_dry;

config = tailsitter.config;

    
function wing_wet = getWetWing( tailsitter )

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

wing_dry = tailsitter.aero.wing;

wing_wet = wing_dry;

config = tailsitter.config;

y_motor = config.propPos_c(2,:);

c_in = wing_dry.geometry.c/((1+wing_dry.geometry.z)/2);
chord_motor = c_in * ( 1- y_motor(2)/(wing_dry.geometry.b/2)*(1-wing_dry.geometry.z) );

prop_name_split = strsplit(tailsitter.prop.name,'x');
prop_diameter = 0.0254 * str2double(prop_name_split{1});

% Calculate diameter of slipstream behind propeller based on v_i_gain
v_i_gain = tailsitter.aero.v_i_gain;
slipstream_diameter = prop_diameter * sqrt( 1/v_i_gain );

wing_wet.geometry.S = 2 * slipstream_diameter * chord_motor;
wing_wet.flap.eta_0 = slipstream_diameter / (wing_dry.geometry.b/2);
% wing_wet.flap.x = wing_dry.flap.x * 1.1;

wing_wet = simpleWingSetFlapEffectiveness( wing_wet );

wing_wet.xyz_cntrl_pt_wing(2,:) = y_motor;
wing_wet.xyz_cntrl_pt_wing(1,:) = - y_motor(2)*sin(wing_dry.geometry.phi) - chord_motor/2;

wing_wet.xyz_wing_np(2,:) = y_motor;


end