%_______________________________________________________________________________
% This program calculates the longitudinal and lateral A and B matrices of
% an aircraft at a given flight condition. The user must specify the mass and
% geometry data, and the atmospheric data and aerodynamic data at the flight
% condition of interest.  The data is saved to a temporary data file and then
% downloaded to the M-files "Long" and "Lat".

% INSTRUCTIONS FOR USE
%
%      1. MODIFY PARAMATER VALUES AS NECESSARY
%      2. CHOOSE "SAVE AS" FROM THE FILE MENU AND RENAME FILE

%*********************************NOTE******************************************
% 1. ALL PARAMETERS SHOULD BE ENTERED IN ENGLISH UNITS. APPROPRIATE UNITS ARE
%    INDICATED AS NECESSARY. IT IS ESSENTIAL THAT THE NAMES OF THE PARAMETERS
%    REMAIN UNCHNGED FOR THE PROGRAM TO FUNCTION PROPERLY. DO NOT CHANGE THE
%    PARAMETER NAMES BUT ONLY PARAMETER VALUES!!!!!!
% 2. BE SURE TO RENAME THE FILE AFTER YOU HAVE MODIFIED IT IN ORDER TO PRESERVE
%    THE ORIGINAL DATA
%*******************************************************************************
	    g=32.174;
%_______________________________________________________________________________
%                          FLIGHT CONDITION
%_______________________________________________________________________________
% Air density [slugs / cubic feet]
     rho = 0.00028652;
% Sound Speed [ft/s]
     a = 968.08;
% Mach number
     M = 1.8;
% Flight Path Angle [deg]
     theta0 = 0.0;
		theta0 = theta0*pi/180;
		u0 = a*M;
     Q = 0.5*rho*u0^2; 
%_______________________________________________________________________________
%																										MASS and GEOMETRY PROPERTIES
%_______________________________________________________________________________
% Aircraft weight [lbs]
     W = 16300;
        m = W/g;
% Aircraft moments of inertia [slugs-sq.ft.]
     Ix = 3549;
     Iy = 58611;
     Iz = 59669;
% Aircraft product of inertia [slugs-sq.ft.]
	 Izx = 0;
% Aircraft wing reference area [sq.ft.]
	 S = 196.1;
	    QS=Q*S;
% Aircraft mean wing chord [ft]
	 cbar=9.55;
% Aircraft wing span [ft]
	 b = 21.94;
%_______________________________________________________________________________
%                          LONGITUDINAL AERODYNAMIC DATA
%_______________________________________________________________________________
CLo = 0.20;
CDo = 0.055;
CLalpha = 2.0;
CDalpha = 0.38;
CMalpha = -1.3;
CLalphadot = 0.;
CMalphadot = -2.;
CLq = 0;
CMq = -4.8;
CLm = -.2;
CDm = 0.0;
CMm = -.01;
CDdeltae = 0.0;
CLdeltae = 0.52;
CMdeltae = -0.1;
%_______________________________________________________________________________
%						    LATERAL AERODYNAMIC DATA
%_______________________________________________________________________________
CYbeta = -1.0;
CLbeta = -0.09;
CNbeta = 0.24;
CYp = -0.0;
CLp = -0.27;
CNp = -0.09;
CYr = 0.0;
CLr = 0.15;
CNr = -0.65;
CLdeltaa = 0.017;
CNdeltaa = .0025;
CYdeltar = 0.05;
CLdeltar = 0.008;
CNdeltar = -0.04;           
%_______________________________________________________________________________
% DO NOT MODIFY CODE BELOW THIS LINE!!!
%_______________________________________________________________________________%
save newname;
Long;
Lat;
delete newname;
%