For Air: y = 1.4 Question B1 a) With the aid of sketches give a clear account of the operation of convergent nozzles as a function of back pressure. In your answer clearly indicate the critical points (pressure ratios) along the pressure ratio axis. A part of the expansion of new teaching and research facilities at QMUL, a new two dimensional blow- down supersonic jet facility is going to be designed, manufactured and installed at our Whitehead Aeronautical Laboratory, Figure QB1. The design Mach number for this facility is M₁ = 2.0. b) Determine the required area ratio (Aj R=287J/kgK c) What should be the supply pressure to the nozzle (P₁) in order to have a normal shock wave at a Ax) A A₂ location at which the area ratio (- A₁ You may assume P ) for this design Mach number. A₁ A atm d) For part c, what would be the discharge mass flow rate per unit throat area? =105 N/m² and T₁ = 300K. Settling Chamber Ро To is 1.5? Convergent-Divergent Nozzle Ą A A A₁ Schematic of a Supersonic Jet Facility Figure OB1 P atm
For Air: y = 1.4 Question B1 a) With the aid of sketches give a clear account of the operation of convergent nozzles as a function of back pressure. In your answer clearly indicate the critical points (pressure ratios) along the pressure ratio axis. A part of the expansion of new teaching and research facilities at QMUL, a new two dimensional blow- down supersonic jet facility is going to be designed, manufactured and installed at our Whitehead Aeronautical Laboratory, Figure QB1. The design Mach number for this facility is M₁ = 2.0. b) Determine the required area ratio (Aj R=287J/kgK c) What should be the supply pressure to the nozzle (P₁) in order to have a normal shock wave at a Ax) A A₂ location at which the area ratio (- A₁ You may assume P ) for this design Mach number. A₁ A atm d) For part c, what would be the discharge mass flow rate per unit throat area? =105 N/m² and T₁ = 300K. Settling Chamber Ро To is 1.5? Convergent-Divergent Nozzle Ą A A A₁ Schematic of a Supersonic Jet Facility Figure OB1 P atm
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
Related questions
Question
![For Air: y = 1.4
PART B
Question B1
a) With the aid of sketches give a clear account of the operation of convergent nozzles as a function of
back pressure. In your answer clearly indicate the critical points (pressure ratios) along the pressure
ratio axis.
b) Determine the required area ratio
A part of the expansion of new teaching and research facilities at QMUL, a new two dimensional blow-
down supersonic jet facility is going to be designed, manufactured and installed at our Whitehead
Aeronautical Laboratory, Figure QB1. The design Mach number for this facility is M₁ = 2.0.
A
=
A₁ A
R=287J/kg K
A₁
location at which the area ratio (
A₁
c) What should be the supply pressure to the nozzle (P) in order to have a normal shock wave at a
Ax
=) is 1.5?
A
Settling Chamber
Po
To
for this design Mach number.
d) For part c, what would be the discharge mass flow rate per unit throat area?
You may assume P =105 N/m² and To = 300K.
atm
Convergent-Divergent Nozzle
A AX
Schematic of a Supersonic Jet Facility
Figure QB1
P
atm](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F97169250-b02b-4db2-9610-24afc15ffb22%2F846db84e-78f5-415b-9ae3-97868f848d05%2F24dakg2_processed.jpeg&w=3840&q=75)
Transcribed Image Text:For Air: y = 1.4
PART B
Question B1
a) With the aid of sketches give a clear account of the operation of convergent nozzles as a function of
back pressure. In your answer clearly indicate the critical points (pressure ratios) along the pressure
ratio axis.
b) Determine the required area ratio
A part of the expansion of new teaching and research facilities at QMUL, a new two dimensional blow-
down supersonic jet facility is going to be designed, manufactured and installed at our Whitehead
Aeronautical Laboratory, Figure QB1. The design Mach number for this facility is M₁ = 2.0.
A
=
A₁ A
R=287J/kg K
A₁
location at which the area ratio (
A₁
c) What should be the supply pressure to the nozzle (P) in order to have a normal shock wave at a
Ax
=) is 1.5?
A
Settling Chamber
Po
To
for this design Mach number.
d) For part c, what would be the discharge mass flow rate per unit throat area?
You may assume P =105 N/m² and To = 300K.
atm
Convergent-Divergent Nozzle
A AX
Schematic of a Supersonic Jet Facility
Figure QB1
P
atm
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