7.4 A reservoir containing air at 2 MPa is connected to ambient air (y = 1.4) at 101 kPa through a C-D nozzle designed to produce flow at Mach 2.0, with axial flow at the nozzle exit plane. (See Figure P7.4.) Under these conditions, the nozzle is underexpanded, with a Prandtl-Meyer expansion fan at the exit. Find the flow direction after the initial expansion fan. How does this turning angle affect the net axial thrust forces exerted by the fluid on the nozzle? 2 MPa Figure P7.4

Elements Of Electromagnetics
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Please solve this question step by step and in clear writing. There is a sub question related to the main question. PLEASE ANSWER THAT AS WELL. Thanks!

7.4 A reservoir containing air at 2 MPa is connected to ambient air (y = 1.4) at 101 kPa through
a C-D nozzle designed to produce flow at Mach 2.0, with axial flow at the nozzle exit plane.
(See Figure P7.4.) Under these conditions, the nozzle is underexpanded, with a Prandtl-Meyer
expansion fan at the exit. Find the flow direction after the initial expansion fan. How does this
turning angle affect the net axial thrust forces exerted by the fluid on the nozzle?
a = ?
2 MPa
Figure P7.4
Transcribed Image Text:7.4 A reservoir containing air at 2 MPa is connected to ambient air (y = 1.4) at 101 kPa through a C-D nozzle designed to produce flow at Mach 2.0, with axial flow at the nozzle exit plane. (See Figure P7.4.) Under these conditions, the nozzle is underexpanded, with a Prandtl-Meyer expansion fan at the exit. Find the flow direction after the initial expansion fan. How does this turning angle affect the net axial thrust forces exerted by the fluid on the nozzle? a = ? 2 MPa Figure P7.4
This nozzle can be used to propel a rocket. As the rocket rises in altitude
the atmospheric pressure will change. As the atmospheric pressure
changes, the turning angle of the exhaust flow will change. Will the total
thrust experienced by this rocket change? Why?
Transcribed Image Text:This nozzle can be used to propel a rocket. As the rocket rises in altitude the atmospheric pressure will change. As the atmospheric pressure changes, the turning angle of the exhaust flow will change. Will the total thrust experienced by this rocket change? Why?
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