Projeto Conceitual de Aeronaves de Transporte

ctesp = 0.60; % Consumo especifico do motor na espera (loiter)
phi14 = 17.45; % Enflechamento: quarter chord sweepback angle
nedebasa = 0; % underwing engines number
tctip = 0.096; % maximum relative thickness of the tip section
tcroot = 0.123; % maximum relative thickness of the tip section
tcmed = 0.5*(tcroot+tctip); % average section maximum thickness
% Fracoes de massa
ftakeoff = 0.995;
fclimb = 0.980;
fdesc = 0.990;
fpouso = 0.992;
%
mtow = 50000; % Estimativa inicial do MTOW
deltamtow = 1e06;
rangem = rangekm*1000; % (m)
rangealtm = rangealt*nm2km*1000; % (m)
swft2 = sw/(ft2m*ft2m);
%
ncont = 1;
iterplo(1) = 1;
mtowplo(1) = mtow;
%
while deltamtow > 10
mtowlb=mtow*kg2lb; % (lb)
% fracao peso vazio/MTOW
wefrac=wempty(arw,swft2,MMO,mtowlb,T0);
fprintf('\n *** Iteracao no: %g *** \n',ncont)
fprintf('\n Razao peso vazio/peso maximo: %4.3f \n',wefrac)
%
areamolhadaft2=0.0199+0.7531*log10(mtowlb);
areamolhadaft2=10^areamolhadaft2;
cd0=cfe*areamolhadaft2/swft2;
e = oswaldf(MMO, arw, phi14, afilam, tcmed, nedebasa);
masscruzi = mtow*ftakeoff*fclimb;
% **** Fracao de massa no cruzeiro ****
% Calculo do combustivel no primeiro terco do cruzeiro
[mcombc]=cruzeiro(Hcruzi,masscruzi,arw,sw,e,cd0,rangem/4,MMO,ctcruz);
masscruzi34 = masscruzi - mcombc;
% Calculo do combustivel no restante do cruzeiro
[mcombc]=cruzeiro(Hcruz,masscruzi34,arw,sw,e,cd0,3*rangem/4,MMO,ctcruz
);
massfinalcruz=masscruzi34-mcombc;
% **** Fracao de massa na espera ****
k=1/(pi*arw*e);
ldmaxauton=1/(2*sqrt(cd0*k));
tempesperah=tempespera/60;
T1=(tempesperah/ldmaxauton)*ctesp;
fmassesp = 1/exp(T1);
massafinalesp = massfinalcruz*fmassesp;
% **** descida ****
massafinaldescida=massafinalesp*fdesc;
% **** Fracao de massa no cruzeiro para o destino alternativo ****
[mcombc]=cruzeiro(1500,massafinaldescida,arw,sw,e,cd0,rangealtm,0.60,1
.02*ctcruz);