disp(' ')
disp(' ')
disp(' Start Here')
echo on
%
% Lateral-Directional Airplane Stability and Control Analysis
%
% Ref: Airplane Flight Dyanmics and Automatic Flight Controls
%      Part 1, 1994
%      by Jan Roskam
%
% See Data input format of Appendix B
%
% Sample data for LearJet, approach configuration, pages 522-523.
%
% Aircraft and configuration
echo off
aircraft='Learjet 24';
configuration='approach';
disp([aircraft '  ' configuration])
%
% Reference Geometry
S=230		% Wing area, ft*ft
cbar=7		% wing mean geometric chord, ft
span=34		% Wing span, ft
%
% Steady State (Trim) Flight Condition
h=0;		% Altitude, ft
M=.152		% Mach number, nondimensional
U1=170		% True airspeed, ft/sec
qbar=34.3	% Dynamic pressure, lbf/ft*ft
Xcg=.32		% X-location of center of gravity, fraction of cbar
alpha1=5	% Trim angle of attack, degree
gamma1=0   % Trim flight path angle, degree

%
% Mass data
W=13000		% Weight, pounds (lbf)
Ixxb=28000	% X-direction moment of inertia, slug*ft*ft
Iyyb=18800	% Y-direction moment of inertia, slug*ft*ft
Izzb=47000	% Z-direction moment of inertia, slug*ft*ft
Ixzb=1300	% XZ-direction product of inertia, slug*ft*ft
%
% Lateral-Directional Coefficients and Stability Derivatives,
%            nondimensional
Clb=-.173
Clp=-.39
Clr=.45
Cyb=-.73
Cyp=0
Cyr=.4
Cnb=.15
Cntb=0
Cnp=-.13
%Cnr=-.26
%Cnr=-.50
%Cnr=-.40
%Cnr=-.30
%Cnr=-.20
%Cnr=-.70
%Cnr=-.90
%Cnr=-1.50
Cnr=0
%
% Lateral-Directional Control Derivatives
Clda=.149
Cldr=.014
Cyda=0
Cydr=.14
Cnda=-.05
Cndr=-.074
% Miscellaneous inputs
g=32.17;		% Acceleration of gravity, ft/sec*sec