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.
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![Question 14
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.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F77204bae-edf0-4503-b51f-a9e104b41580%2F8af00dd5-ec00-4204-b07b-ac3a190fca53%2Fkwnlgxh_processed.jpeg&w=3840&q=75)
Transcribed Image Text:Question 14
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.
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