The stagnation temperatures at the inlet and exit of a combustion chamber are $600 \mathrm{~K}$ and $1200 \mathrm{~K}$, respectively. If the heating value of the fuel is $44 \mathrm{MJ} / \mathrm{kg}$ and specific heat at constant pressure for air and hot gases are $1.005 \mathrm{~kJ} / \mathrm{kg} . \mathrm{K}$ and $1.147 \mathrm{~kJ} / \mathrm{kg} . \mathrm{K}$ respectively, the fuel-to-air ratio is
(A) 0.0018
(B) 0.018
(C) 0.18
(D) 1.18
The stagnation temperatures at the inlet and exit of a combustion chamber are $600 \mathrm{~K}$ and $1200 \mathrm{~K}$, respectively. If the heating value of the fuel is $44 \mathrm{MJ} / \mathrm{kg}$ and specific heat at constant pressure for air and hot gases are $1.005 \mathrm{~kJ} / \mathrm{kg} . \mathrm{K}$ and $1.147 \mathrm{~kJ} / \mathrm{kg} . \mathrm{K}$ respectively, the fuel-to-air ratio is
(A) 0.0018
(B) 0.018
(C) 0.18
(D) 1.18