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: airfoilAnalytic0515AlFit.m
    path of file: ./repos/LADAC/aerodynamics/airfoil/analytic/analytic_05_15_alpha
    
    the code of the file until where you have to start completion: function [fcl,fcd,fcm] = airfoilAnalytic0515AlFit(alpha_deg,Ma,c_L,c_D,c_m,varargin)
% airfoilAnalytic0515AlFit performs an analytic fit of airfoil coefficients
% data for different angles of attack and Mach numbers.
%   For the analytic fit, the analytic function airfoilAnalytic0515De is
%   used.
% 
% Inputs:
%   alpha_deg      	angle of attack (1xN array), in deg

    
function [fcl,fcd,fcm] = airfoilAnalytic0515AlFit(alpha_deg,Ma,c_L,c_D,c_m,varargin)
% airfoilAnalytic0515AlFit performs an analytic fit of airfoil coefficients
% data for different angles of attack and Mach numbers.
%   For the analytic fit, the analytic function airfoilAnalytic0515De is
%   used.
% 
% Inputs:
%   alpha_deg      	angle of attack (1xN array), in deg
%   Ma             	Mach number (1xN array), dimensionless
%   c_L            	lift coefficient (1xN array), dimensionless
%   c_D           	drag coefficient (1xN array), dimensionless
%   c_m            	pitching moment coefficient (1xN array), dimensionless
%   vis_flag       	flag if analytic fit should be visualized (scalar
%                  	bolean)
% 
% Outputs:
%   fcl             solution for the analtic function coefficients for
%                 	the lift coefficient (6x1 array or 6xN array):
%                       fcl(1,:):  	alpha_0
%                       fcl(2,:):  	lift curve slope for Ma=0 and c_L=0
%                       fcl(3,:):  	magnitude of stall lift coefficient (usually 
%                                   negative)
%                       fcl(4,:):  	angle of attack where the mean stall occurs
%                       fcl(5,:):  	additional correction factor for Prandtl-
%                                   Glauert factor (usually close to 1)
%                       fcl(6,:):  	abruptness factor of the stall onset
%   fcd            	solution for the analtic function coefficients for
%                 	the drag coefficient (6x1 array or 6xN array):
%                       fcd(1,:): 	minimum drag coefficient
%                       fcd(2,:): 	multiplicator for parabola
%                       fcd(3,:): 	angle of attack, where the minimum drag 
%                                   coefficient occurs
%                       fcd(4,:):  	steepness of the drag increase due to stall
%                       fcd(5,:): 	angle of attack where the attached flow and
%                                   detached flow
%                                   models are blend