Projeto Conceitual de Aeronaves de Transporte

massafinalcruzalt=massafinaldescida-mcombc;
%
%fmasstot=ftakeoff*fclimb*fmasscruz*fmassesp*fdesc*fpouso*fcruzalt;
% massa final 2a descida (nivel do mar)
massafinal2adesc=fdesc*massafinalcruzalt;
% Pouso
massafinalpouso=massafinal2adesc*fpouso;
% fracao de combustivel consumido na missao
mfuel = mtow-massafinalpouso+wfuelmanobra;
mfuel = mfuel*1.005; % 0.5% of trapped fuel
wfuelfrac=mfuel/mtow;
% recalculo do MTOW
mtownew = (wcrew+wmpayload)/(1-(wefrac+wfuelfrac));
deltamtow = abs(mtownew-mtow);
mtow
= 0.50*(mtow+mtownew);
ncont = ncont +1;
iterplo(ncont) = ncont;
mtowplo(ncont) = mtow;
end
fprintf('\n Peso Máximo de Decolagem (MTOW) = %6.0f kg \n',mtow)
figure(1)
plot(iterplo,mtowplo,'--rx','LineWidth',2)
xlabel('Iteração','fontsize',14)
ylabel('MTOW (kg)','fontsize',14)
grid on
function e=oswaldf(Mach,AR,phi14,afilam,tcmed,nedebasa)
% Oswald's factor calculation
rad = pi/180;
%
aux1 = 1+0.12*Mach^6;
aux2 = 0.1*(3*nedebasa+1)/((4+AR)^0.8);
fy = 0.005*(1+1.5*(afilam-0.6)^2);
aux3 = (0.142+ fy*AR*((10*tcmed)^0.33))/(cos(phi14*rad)^2);
e = 1/(aux1*(1+aux2+aux3));
function [mcombc]=cruzeiro(Hft,masscruzi,arw,sw,e,cd0,rangem,Mamax,ct)
% calcula fracao de massa em perfil de cruzeiro de longo alcance
atm=atmosfera(Hft,0);
rhoi = atm(6);
vsomi = atm(7);
%
cl_long = sqrt(pi*e*arw*cd0/3);
cd = 4*cd0/3;
%
% Velocidade de cruzeiro de longo alcance
vcruzi=sqrt(masscruzi*9.81/(0.50*rhoi*cl_long*sw));
machi=vcruzi/vsomi;
if machi > Mamax
vcruzi=Mamax*vsomi;
cl_long=masscruzi*9.81/(0.50*rhoi*sw*vcruzi*vcruzi);
cd=cd0 + cl_long^2/(pi*arw*e);
end
% calculo da massa de combustivel consumida
t1=sqrt(2/(rhoi*sw));