Demo JetEngineAnalysis

Plot specific thrust as a function of mach number and combustion temperature ------------------------------------------------------------------------ See also JetEngineAnalysis, Plot2D ------------------------------------------------------------------------

%--------------------------------------------------------------------------
%   Copyright (c) 2003 Princeton Satellite Systems, Inc.
%   All rights reserved.
%--------------------------------------------------------------------------

p               = struct;
p.tT4           = [1600 1900 2200];
p.altitude      = 12000;
p.machNo        = linspace(0.3,5);
d               = struct;
d.cPC           = 1004;
d.cPT           = 1004;
d.hPR           = 42800000;
d.gammaT        = 1.4;
d.units         = 'mks';
d.eD            = 1.0;
d.etaB          = 1.0;
d.piB           = 1.0;
d.piDMax        = 1.0;
d.piN           = 1.0;
d.p0OverP9      = 1.0;
d.analysis      = 'real';
d.engine        = 'ramjet';
d.m2            = 0.4;

fprintf(1,'Analyzing %d Mach numbers...\n',length(p.machNo));
for k = 1:length(p.machNo)
  g = JetEngineAnalysis(p,d);
end

Plot2D(p.machNo,g.fOverMDotA,'M','F/mDot*Area','Jet Engine Analysis')
legend('1600 K','1900 K','2200 K')



%--------------------------------------

Analyzing 100 Mach numbers...