(b) The upstream of the isentropic air flow convergent-divergent nozzle at section (1), V=188 m/s, Pr= 130 kPa, and T= 28°C, as shown in Figure 2. Consider the discharge flow is supersonic and the throat area is 0.1 m². Assume y= 1.4 and R= 287 J/kg.K.
(b) The upstream of the isentropic air flow convergent-divergent nozzle at section (1), V=188 m/s, Pr= 130 kPa, and T= 28°C, as shown in Figure 2. Consider the discharge flow is supersonic and the throat area is 0.1 m². Assume y= 1.4 and R= 287 J/kg.K.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
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![(b) The upstream of the isentropic air flow convergent-divergent nozzle at section (1),
V=188 m/s, Pr= 130 kPa, and T= 28°C, as shown in Figure 2. Consider the
discharge flow is supersonic and the throat area is 0.1 m² Assume y= 1.4 and
R= 287 J/kg.K.
High Pressure
Low Velocity
Low Pressure
High Velocity
Gases
Gases
Subsonic
Supersonic
Throat
(1).
Convergent Section
(2)
Divergent Section
Figure 2
[Gambarajah 2]
Determine the Mach number at section (1).
(ii)
Determine the stagnation temperature and pressure.
(iii) Calculate the pressure, density and velocity at throat area of convergent-
divergent nozzle.
(iv) Calculate the mass flow rate in kg/s for the flow.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F2b821139-cf08-406b-baa0-1f003c469379%2F8f302542-1bba-466c-aa84-17b4237fdee9%2Fdgurlpf_processed.jpeg&w=3840&q=75)
Transcribed Image Text:(b) The upstream of the isentropic air flow convergent-divergent nozzle at section (1),
V=188 m/s, Pr= 130 kPa, and T= 28°C, as shown in Figure 2. Consider the
discharge flow is supersonic and the throat area is 0.1 m² Assume y= 1.4 and
R= 287 J/kg.K.
High Pressure
Low Velocity
Low Pressure
High Velocity
Gases
Gases
Subsonic
Supersonic
Throat
(1).
Convergent Section
(2)
Divergent Section
Figure 2
[Gambarajah 2]
Determine the Mach number at section (1).
(ii)
Determine the stagnation temperature and pressure.
(iii) Calculate the pressure, density and velocity at throat area of convergent-
divergent nozzle.
(iv) Calculate the mass flow rate in kg/s for the flow.
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