If the rocket exhaust gases are calorically perfect and have a mean mo – McqOptions

MCQOPTIONS

1.	If the rocket exhaust gases are calorically perfect and have a mean molecular mass of 28 kg/kmol, and a constant specific heat ratio ( ) of 1.33, determine the nozzle exit velocity. Assume the nozzle inlet conditions to be the following: P1 = 5 MPa, V1 = 240 m/s, T1 = 750 K and exit pressure (Pe) to be 1 MPa.
A.	204 m/s
B.	699.21 m/s
C.	712.32 m/s
D.	805.56 m/s
Answer» E.

Discussion

No Comment Found

Related MCQs

What will happen if the maximum theoretical nozzle exhaust velocity tends to a very large value?
What is the pressure ratio for the maximum theoretical value of nozzle outlet velocity?
What is the expression for the maximum theoretical value of the nozzle outlet velocity (ve) with an infinite expansion, if represents the ratio of specific heats, To represents the chamber temperature, R is the gas constant?
What are the standardized chamber pressure and exit pressure values used for comparing the specific impulse values or various design parameters of different rocket engines?
Which of the following will improve the performance of a rocket engine?
What is the correct definition of the nozzle area expansion ratio?
The area of a de Laval Nozzle is directly proportional to the ratio v/V, where v is the flow velocity and V is the specific volume.
If the rocket exhaust gases are calorically perfect and have a mean molecular mass of 28 kg/kmol, and a constant specific heat ratio ( ) of 1.33, determine the nozzle exit velocity. Assume the nozzle inlet conditions to be the following: P1 = 5 MPa, V1 = 240 m/s, T1 = 750 K and exit pressure (Pe) to be 1 MPa.
If at a point along the isentropic rocket nozzle, the temperature of the gas is 718 K, and the flow velocity is 150 m/s, determine the nozzle exit velocity, given the exhaust gas temperature is 460 K (Assume Cp = 1005 J/kg K)
Which of the following will happen if there is a flow obstruction in the nozzle inner wall?