[mouli1991]

Dear sir/mam
i am new to analysis...im actually carrying out rocket nozzle analysis.. i need a help here..i have exit mach number as 4.8 and divergent angle as 15 degree and i calculated length of divergent section as Ld=(re-rt)cot theta (re- radius of exit and radius of throat)
now i have from a literature as
Inlet Total pressure-44.10 bar
Inlet total temp - 3400K
Mass flow inlet-826 kg/s
for this parameters they calculated
Ae=0.8612 m
At = 0.340 m
divergent angle as 15 degree
now i calculated using isentropic relations (area ratio, p0/pt etcc,,,)
i cant get the same area values using above conditions
i took exit mach as 4.8 from there i started
please help and solve my problem...