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.
Related questions
Question
100%
B6

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.
Expert Solution

This question has been solved!
Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.
This is a popular solution!
Trending now
This is a popular solution!
Step by step
Solved in 2 steps
