function c = f16_massprop;
%
%  function c = f16_massprop
%
%  Usage: c = f16_massprop
%
%  Description:
%
%    Computes mass properties for the f-16 nonlinear model.
%
%  inputs:
%    
%    None.
%
%  outputs:
%
%      c  = c(1) through c(9) = inertia constants for aircraft
%           nonlinear equations of motion.
%           c(10) = aircraft mass.
%           c(11) = X c.g. position in fraction of the m.a.c.
%
%
g=32.174;			% gravitational constant, ft/sec^2
mass=20500.0/g;			% mass of the aircraft, slugs
xcg= 0.35;			% location of center of mass
ixx=9496.0;			% inertial parameters
iyy=55814.0;
izz=63100.0;
ixz=982.0;

%
% Compute the parameters expected by f16_deq()
%
c=zeros(11,1);
gam=ixx*izz-ixz^2;
c(1)=((iyy-izz)*izz-ixz^2)/gam;
c(2)=(ixx-iyy+izz)*ixz/gam;
c(3)=izz/gam;
c(4)=ixz/gam;
c(5)=(izz-ixx)/iyy;
c(6)=ixz/iyy;
c(7)=1.0/iyy;
c(8)=(ixx*(ixx-iyy)+ixz^2)/gam;
c(9)=ixx/gam;
c(10)=mass;
c(11)=xcg;

return

