(3.b) A converging-diverging nozzle is designed to expand air from a chamber in which the pressure is 750 kN/m² and the temperature 35°C to give a Mach number of 2.9 at the exit plane. The throat area of the nozzle is 0.07 m². For air y=1.4 and R=287 Jkg-¹K-¹. Calculate: (i) (ii) (iii) (iv) The exit area of the nozzle. The mass flow rate through the nozzle when operating under design conditions. The design back pressure to operate with a Mach number of 2.9 at the exit plane. The back pressure below which there are no shock waves in the nozzle.
(3.b) A converging-diverging nozzle is designed to expand air from a chamber in which the pressure is 750 kN/m² and the temperature 35°C to give a Mach number of 2.9 at the exit plane. The throat area of the nozzle is 0.07 m². For air y=1.4 and R=287 Jkg-¹K-¹. Calculate: (i) (ii) (iii) (iv) The exit area of the nozzle. The mass flow rate through the nozzle when operating under design conditions. The design back pressure to operate with a Mach number of 2.9 at the exit plane. The back pressure below which there are no shock waves in the nozzle.
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
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I need help on 3b
Transcribed Image Text:Question 3
(3.a) A gas with a molar mass of 40 kg/kmole and a specific heat ratio y=1.67 flows
isentropically through a venturi meter. At the inlet, the velocity is 135 m/s, the
pressure 120 kPa and the temperature 20°C. At the throat the temperature is
found to be -20°C.
(i) Determine the Mach number at the inlet.
(ii)
(3.b) A converging-diverging nozzle is designed to expand air from a chamber in which
the pressure is 750 kN/m² and the temperature 35°C to give a Mach number of
2.9 at the exit plane. The throat area of the nozzle is 0.07 m².
For air y=1.4 and R=287 Jkg-¹K-¹.
Calculate:
(i)
(ii)
(iii)
Find the Mach number, pressure and velocity at the throat.
(iv)
The exit area of the nozzle.
The mass flow rate through the nozzle when operating under design
conditions.
The design back pressure to operate with a Mach number of 2.9 at the exit
plane.
The back pressure below which there are no shock waves in the nozzle.
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