function [constant]=Cessna182
% function [constant]=Cessna182
% 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 Cessna 182 at cruise, Vt=220.1 ft/sec, Hp=5000 ft.')
% Mass related inputs
constant(1)=2650;      % W, Weight, pounds (lbf)
constant(2)=32.17405;  % g, Acceleration of gravity, ft/(sec*sec)
constant(3)=constant(1)/constant(2); % mass, slugs
constant(4)=948;    % Ixx, slug*ft*ft
constant(5)=1346;   % Iyy, slug*ft*ft
constant(6)=1967;   % Izz, slug*ft*ft
constant(7)= 0;     % Ixz, slug*ft*ft
constant(8)=.70;    % 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)=174;    % S, wing area, ft^2
constant(21)=4.9;    % cbar, mean geometric chord, ft
constant(22)=36;     % b, wing span, ft
constant(23)=0;      % 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)=0.0223; % CDm, CD for minimum drag
constant(26)=0.0554; % k
constant(27)=0;      % CLdm, CL at the minimum drag point

% Lift Force
constant(28)=0.307;  % CL0
constant(29)=4.41;   % CLalpha
constant(30)=0.43;   % CLdeltaE
constant(31)=1.7;    % CLalphadot
constant(32)=3.9;    % CLQ
% Side Force
constant(33)=0;      % CY0
constant(34)=-0.393; % CYbeta
constant(35)=0;      % CYdeltaA
constant(36)=0.187;  % CydeltaR
constant(37)=-0.075; % CYP
constant(38)=0.214;  % CYR
% Rolling Moment
constant(39)=0;       % Cl0
constant(40)=-0.0923; % Clbeta
constant(41)=0.229;   % CldeltaA
constant(42)=0.0147;  % CldeltaR
constant(43)=-0.484;  % ClP
constant(44)=0.0798;  % ClR
% Pitching Moment
constant(45)=0.04;   % CM0
constant(46)=-0.613; % Cmalpha
constant(47)=-1.122; % CMdeltaE
constant(48)=-7.27;  % CMalphadot
constant(49)=-12.4;  % CMQ
% Yawing Moment
constant(50)=0;       % CN0
constant(51)=0.0587;  % CNbeta
constant(52)=-0.0216; % CNdeltaA
constant(53)=-0.0645; % CNdeltaR
constant(54)=-0.0278; % CNP
constant(55)=-0.0937; % CNR
% Reference positions
constant(56)=.264; % XbarRef, nondimensional
constant(57)=.264; % XbarCG,  nondimensional

% Trim conditions. These may or not be used by subsequent programs. Small 
% variations in these trim flight conditions are OK.
constant(58)=220.1; % trim speed, Vt, ft/sec
constant(59)=5000;  % 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)=0;     % 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

