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: wingGetDimlessIndVel.m
    path of file: ./repos/LADAC/aerodynamics/vlm_wing/geometry
    
    the code of the file until where you have to start completion: function [v_b,v_t] = wingGetDimlessIndVel( V_inf_local, geometry, wake, Ma, is_unsteady )
% wingGetDimlessIndVel computes the dimensionless induced velocity for a
% unit circulation normalized by the wing span.
%   The implementation of [1], eq. (6) is used. As we assume that no
%   segment of the horseshoe vortices is crossing a control point and the
%   control points do not lie on the bound segment of the horseshoe
%   vortices, we only use the i~=j part and not the i=j part of [1], eq.
%   (6).
%   Moreover, since it is very common, the dimensionless induced velocity
%   is not normalized by the local chord but by the wing span.
% 
% Inputs:
%   V_inf_local         local free-stream velocity for each panel, signs
%                       are defined for how the vector is seen by the plane
%                       (3xn array)
%   geometry            Wing geometry
%                       (struct, see: wingSetGeometry)
%   
% Outputs:
%   v                   dimensionless induced velocity (unit circulation
%                       and normalized by the wing span)
%                       (3 x Nc x Nv array, where Nc is the number of
%                       control points and Nv is the number of horseshoe
%                       vortices)
% 
% Literature:
%   [1] Phillips, W. F., & Snyder, D. O. (2000). Modern adaption of
%       Prandtl's classic lifting-line theory. Jounal of Aircraft, 37(4),
%       662-670.
% 

    
function [v_b,v_t] = wingGetDimlessIndVel( V_inf_local, geometry, wake, Ma, is_unsteady )
% wingGetDimlessIndVel computes the dimensionless induced velocity for a
% unit circulation normalized by the wing span.
%   The implementation of [1], eq. (6) is used. As we assume that no
%   segment of the horseshoe vortices is crossing a control point and the
%   control points do not lie on the bound segment of the horseshoe
%   vortices, we only use the i~=j part and not the i=j part of [1], eq.
%   (6).
%   Moreover, since it is very common, the dimensionless induced velocity
%   is not normalized by the local chord but by the wing span.
% 
% Inputs:
%   V_inf_local         local free-stream velocity for each panel, signs
%                       are defined for how the vector is seen by the plane
%                       (3xn array)
%   geometry            Wing geometry
%                       (struct, see: wingSetGeometry)
%   
% Outputs:
%   v                   dimensionless induced velocity (unit circulation
%                       and normalized by the wing span)
%                       (3 x Nc x Nv array, where Nc is the number of
%                       control points and Nv is the number of horseshoe
%                       vortices)
% 
% Literature:
%   [1] Phillips, W. F., & Snyder, D. O. (2000). Modern adaption of
%       Prandtl's classic lifting-line theory. Jounal of Aircraft, 37(4),
%       662-670.
% 

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

% Ma = 0.7417*0;
% Ma = 0.6928*0;
% Ma = 0.6128*0;
% Ma(:) = cosd(22)*0.8;
beta_Ma = 1./sqrtReal(1-Ma.^2);
cntrl_pt = geometry.ctrl_pt.pos + V_inf_local .* 0.5 .* geometry.ctrl_pt.c .* ( beta_Ma - 1 );
geometry.vortex.pos(:,:,2:end