Air at a static temperature and pressure of 9°C and 98 kPa respectively enters the intake of an aircraft gas turbine engine with a velocity of 198 m/s. The intake may be regarded as a diffuser with an inlet area of 0.3 m2 and an exit area that reduces the air flow velocity essentially to zero. Calculate the mass flow rate (kg/s) of air through the intake, given the specific gas (air) constant as 287 J/(kg.K), keeping three decimal places.

Air at a static temperature and pressure of 9°C and 98 kPa respectively enters the intake of an aircraft gas turbine engine with a velocity of 198 m/s. The intake may be regarded as a diffuser with an inlet area of 0.3 m2 and an exit area that reduces the air flow velocity essentially to zero. Calculate the mass flow rate (kg/s) of air through the intake, given the specific gas (air) constant as 287 J/(kg.K), keeping three decimal places.