(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

See similar textbooks

Similar questions

Example: Carbon dioxide flows steadily at a mass flow rate of 3 kg/s and pressure of 1400 kPa and 200°C with a low velocity. It expands after the nozzle to a pressure of 200 kPa. The duct is designed so that the flow can be approximated as isentropic. Determine the density, velocity, flow area, and Mach number at each location along the duct that corresponds to a pressure drop of 200 kPa
In compressible flow, velocity measurements with a Pitot probe can be grossly in error if relations developed for incompressible flow are used. Therefore, it is essential that compressible flow relations be used when evaluating flow velocity from Pitot probe measurements. Consider supersonic flow of air through a channel. A probe inserted into the flow causes a shock wave to occur upstream of the probe, and it measures the stagnation pressure and temperature to be 620 kPa and 340 K, respectively. If the static pressure upstream is 110 kPa, determine the flow velocity.
When a pitot-static tube is placed in a supersonic flow, the probe reads P = 190 kPa and P = 150 kPa. If the stagnation temperature is 400 K, estimate the freestream Mach number and velocity.
Q3/ Air at 200 kPa, 100 °C, and Mach number Ma=0.8 flows through a duct. Calculate thevelocity, the stagnation pressure and the stagnation temperature of the air.
Calculate the stagnation temperature and pressure for the following substances flowing through a duct: (a) helium at 0.25 MPa, 50°C, and 290 m/s; (b) nitrogen at 0.15 MPa, 50°C, and 300 m/s; and (c) steam at 0.1 MPa, 350°C, and 340 m/s.
Air enters a diffuser with a velocity of 200m/s. Determine the speed of sound Mach number at the diffuser inlet at 30°C
The entropy increase across a normal shock wave is 199.5 J/(kg · K). Whatis the upstream Mach number?
A uniform supersonic flow of air at Mach 3.8, with a stagnation pressure of 5.0 MPa and stagnationtemperature of 1100 K, expands around a 23o convex corner. Determine the downstream Mach
If the exit Mach number in Fig. is 2.2, what is theexit area?(a) 0.10 m2, (b) 0.12 m2, (c) 0.15 m2, (d ) 0.18 m2, (e) 0.22 m2
Air at 200 kPa, 100°C, and Mach number Ma = 0.8 flows through a duct. Calculate the velocity and the stagnation pressure, temperature, and density of the air.
A flow of air with Mach number M1 = 2, pressure p1 = 0.7 atm, and temperature 630 degR is turned away from itself through an angle of 26.38 deg. Determine the Mach number, the staticpressure, the static temperature, and the stagnation pressure after the turn (all pressures in atm).Also determine the Mach angles at the beginning and end of the expansion fan.
A gas at a specified stagnation temperature and pressure is accelerated to Ma = 2 in a converging–diverging nozzle and to Ma = 3 in another nozzle. What can you say about the pressures at the throats of these two nozzles