function [constant]=BoilEX
% this is the altered version for Boiler Express, 04/01

% function [constant]=BoilEX
% Version 1.0, 2/14/01
% Make a vector of constants for the Cessna 182 aircraft
% for the cruise configuration. Ref Roskam Page 480
% The order of these constants is critical. Do not change the order
% or code in other simulation functions will be in error.

disp('Input constants for the Boiler Express at cruise, Vt=28 ft/sec, Hp=1000 ft.')
% Mass related inputs
constant(1)=10.25;         % W, Weight, pounds (lbf)
constant(2)=32.17405;  		% g, Acceleration of gravity, ft/(sec*sec)
constant(3)=constant(1)/constant(2); % mass, slugs
%moments of inertia calculated from code by Jeremy Davis and Daniel Squibb
constant(4)=2.2176;    		% Ixx, slug*ft*ft
constant(5)=18.7568;   		% Iyy, slug*ft*ft
constant(6)=20.7513;   		% Izz, slug*ft*ft
constant(7)= 1.1805;     	% Ixz, slug*ft*ft
%constant(7)= 0;     		% Ixz, slug*ft*ft
constant(8)=.5070;    		% propeller efficiency, eta, nondimensional
%constant(9)=; 				% unassigned

% Derived constants from the inertia data
constant(10)=constant(4)*constant(6)-constant(7)*constant(7);  %gamma
constant(11)=((constant(5)-constant(6))*constant(6)-constant(7)*constant(7))/constant(10);% c1
constant(12)=(constant(4)-constant(5)+constant(6))*constant(7)/constant(10);% c2
constant(13)= constant(6)/constant(10);% c3 
constant(14)= constant(7)/constant(10);% c4 
constant(15)=(constant(6)-constant(4))/constant(5);% c5 
constant(16)= constant(7)/constant(5);% c6
constant(17)= 1/constant(5);% c7
constant(18)=  (constant(4)*(constant(4)-constant(5))+constant(7)*constant(7))/constant(10);% c8 
constant(19)=  constant(4)/constant(10);% c9 

% aircraft geometry
constant(20)=15.11;          % S, wing area, ft^2
%S was 13.5 in report, measured and calculated here came out with 2+ extra square feet
constant(21)=(1.4+.95)/2;    % cbar, mean geometric chord, ft
constant(22)=12.84;    		  % b, wing span, ft
constant(23)=0.08307;        % phiT, thrust inclination angle, RADIANS
constant(24)=0;      		  % dT, thrust offset distance, ft

% Nondimensional Aerodynamic stability and control derivatives

% Drag Polar CD=k(CLstatic-CLdm)^2 + CDm
constant(25)=0.028; 		% CDm, CD for minimum drag from fig. 3.5 in boiler express report
constant(26)=.0389; 		% k calculated using 1/(pi*AR*e)
constant(27)=0.6;       % CLdm, CL at the minimum drag point from fig. 3.5 in boiler express report

% Lift Force
constant(28)=.7496;  	% CL0 from figure 3.4 in report
constant(29)=4.9392;    % CLalpha
constant(30)=0.3740;    % CLdeltaE
constant(31)=1.8094;    % CLalphadot
constant(32)=2.9699;    % CLQ
% Side Force
constant(33)=0; 	     % CY0
constant(34)=-2.8192;  % CYbeta
%constant(34)=-.0484;  % CYbeta %old
constant(35)=0;        % CYdeltaA
%left CydR the same too code said 0
constant(36)=-0.0403;  % CydeltaR
constant(37)=-0.7192;  % CYP
constant(38)=0.0269;   % CYR
% Rolling Moment
constant(39)=0;        % Cl0
constant(40)=-1.394;   % Clbeta
constant(41)=0;   	  % CldeltaA
constant(42)=0;        % CldeltaR
constant(43)=-0.6785;  % ClP
constant(44)=1.8799;   % ClR
% Pitching Moment
constant(45)=0;  		  % CM0
constant(46)=-0.048;   % Cmalpha
constant(47)=-.7149;   % CMdeltaE
constant(48)=-.008;    % CMalphadot
constant(49)=0.5611;   % CMQ
% Yawing Moment
constant(50)=0;  	     % CN0
constant(51)=0.2284;   % CNbeta
constant(52)=0; 		  % CNdeltaA
constant(53)=0.1889;   % CNdeltaR
constant(54)=3.2556;   % CNP
constant(55)=-31.6033; % CNR

% Reference positions
constant(56)=0.35; % XbarRef, nondimensional - from report
constant(57)=0.35; % XbarCG,  nondimensional - from report

% Trim conditions. These may or not be used by subsequent programs. Small 
% variations in these trim flight conditions are OK.
constant(58)=28; % trim speed, Vt, ft/sec
constant(59)=1000;  % Trim altitude, ft
constant(60)=0;     % Trim alpha, >>>DEGREES<<<This is not used by CessnaLongSC
% The constants below are used only by CessnaLongSC and CessnaLatSC
constant(61)=9.698e-04;     % CLu=0
constant(62)=0;     % CDu=0
constant(63)=-.096; % CTxu
constant(64)=0;     % Cmu
constant(65)=0;     % CmTu
constant(66)=0;     % CmTalpha
constant(67)=0;     % CDdeltae
