suhpaconstraints.m

function [C,Ceq]=suhpaconstraints(x)
% SUHPACONSTRAINTS calculates the SUHPA constraints
%   [C,Ceq]=SUHPACONSTRAINTS(X) returns a vector C, with C(1)<1 if the tip
%   deflection constraint is satisfied and C(2)<1 if the wing thickness
%   constraint is satisfied. Ceq is set to zero (satisfied). The wing is
%   defined by X, in the same way as for SUHPADRAG. The first three 
%   elements of the X imput vector are the span [m] and the root and tip 
%   thickness to chord ratio, respectively.
%
%   If wingParameters.foil='naca44xx', no further inputs are required
%
%   If wingParameters.foil='nacaxxxx', the 4th and 5th elements of X are
%   the maximum camber and its location (as per the first two-digits of the
%   NACA 4-digit definition.
%
%   If wingParameters.foil='hermite', X may have either 9 elements (with
%   X(4:9) being the hermite foil definition of a constant aerofoil
%   throughout the span) or 27 elements (with X(4:9), X(10:15), X(16:21)
%   and X(22:27) being the hermite foil defintion at the root, b/6, b/3 and
%   b/2 locations along span b - with linear variation between aerofoils).
%   The six hermite foil variables are (suggested ranges in brackets):
%    1  tension_upper_nose [0.1,0.4] |T_A^upper|
%    2  tension_lower_nose [0.1,0.4] |T_A^lower|
%    3  tension_upper_tail [0.1,2] |T_B^upper|
%    4  tension_lower_tail [0.1,2] |T_B^lower|
%    5  angle_lower_tail (deg) [-15,15] alpha_c
%    6  angle_tail (deg) [1,30] alpha_b
%
%   Further global variables need to be set before calling
%   SUHPACONSTRAINTS: wingParameters.weight (aircraft weight minus wing
%   weight [N]), wingParameters.loading (wing loading [N/m^2])
%   wingParameters.foil (aerofoil type).
%
% -------------------------------------------------------------------------
% Aircraft Geometry Toolbox v0.1.0, Andras Sobester 2014.
%
% Sobester, A, Forrester, A I J, "Aircraft Aerodynamic Design - Geometry 
% and Optimization", Wiley, 2014.
% -------------------------------------------------------------------------
%
% Copyright 2014 A I J Forrester
%
% This program is free software: you can redistribute it and/or modify  it
% under the terms of the GNU Lesser General Public License as published by
% the Free Software Foundation, either version 3 of the License, or any
% later version.
% 
% This program is distributed in the hope that it will be useful, but
% WITHOUT ANY WARRANTY; without even the implied warranty of
% MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the GNU Lesser
% General Public License for more details.
% 
% You should have received a copy of the GNU General Public License and GNU
% Lesser General Public License along with this program. If not, see
% <http://www.gnu.org/licenses/>.

global wingParameters
tipDef=wingdeflection(x);
C(1)=tipDef-wingParameters.deflection;
C(2)=thickness(x);
Ceq=0;