function plane = input_param
%input parameters for airplane


    answerX={'100','3950','6600','5000','45000','2200','34000','0.25','50'};
    
    v0 = str2double(answerX{1});
    h = str2double(answerX{2});
    m = str2double(answerX{3});
    Jxx = str2double(answerX{4});
    Jyy = str2double(answerX{5});
    Jxy = str2double(answerX{6});
    Jzz = str2double(answerX{7});
    x_T = str2double(answerX{8});
    Tsim =  str2double(answerX{9});        



vyska = h;
T_0         = 15;          % teplota [°]
dTdh        = 6.51122e-3;  % teplotni gradient [°/m]
rho_0       = 1.2250;      % hustota vzduchu [kg/m^3]
if vyska < 11000
	T     = T_0 - dTdh*vyska;
else
	T     = -56.5;
end
a = 331.3+(0.607*T);
rho = rho_0*(1-vyska/44308)^4.2553;

    
plane.m   = m;      % hmotnost letadla
plane.h   = h;      % vyska letu
plane.v0  = v0;     % rychlost letu
plane.Jxx = Jxx;    % moment setrvacnosti pro osu x
plane.Jyy = Jyy;    % moment setrvacnosti pro osu y
plane.Jzz = Jzz;    % moment setrvacnosti pro osu z
plane.Jxy = Jxy;    % moment setrvacnosti pro osu z
plane.x_T = x_T;    % centrum teziste
plane.M = v0/a    % Machovo cislo
plane.Tsim = Tsim;  % delka simulace
plane.rho = rho;    % hustota vzduchu

disp('-----------------------------------')
disp(sprintf(' Air speed:     %5.1f',v0))
disp(sprintf(' Mach number:   %5.3f',v0/a))
disp(sprintf(' Altitude:      %5.1f',h))
disp(sprintf(' Aircraft mass: %5.1d',m))
disp(sprintf(' Inertia moment Jxx:%5.1d',Jxx))
disp(sprintf(' Inertia moment Jyy:%5.1d',Jyy))
disp(sprintf(' Inertia moment Jzz:%5.1d',Jzz))
disp(sprintf(' Inertia moment Jxy:%5.1d',Jxy))
disp(sprintf(' Center of gravity:%5.3g',x_T))
disp('-----------------------------------')

