% Data is selected to duplicate Roskam figures 4.5


aircraft='Cessna 182, Cruise'
r2d=180/pi;
CL0=.307
CLalpha=4.41/r2d      % Per degree
CLdeltaE=.43/r2d      % Per degree
CLiH=3*CLdeltaE       % Per degree

% Pitching moment about moment reference point specified below
CM0=.04
CMalpha=-.613/r2d    % Per degree
CMdeltaE=-1.122/r2d  %Per degree
CMiH=3*CMdeltaE      %Per degree

%deltaE=[-20 -10 0 10]
deltaE=[-26 -12 0 4 17] % Degree

iH=0             % Degree

mom_ref_pt=.264   % Moment reference point in % chord
forward_cg=.13   % forward cg limit in % chord
aft_cg=.39       % aft cg limit in % chord
alpha_stall=12   % angle of attack (deg) for stall
Cl_PlotMax=1.4   % maximum Cl for plots in figure 2 (the aircraft trim diagram)
alpha_PlotMax=12 % maximum angle of attack (deg) for figure 1
% End of data input section
