1. Air is flowing isentropically through a converging duct which is fed from a large reservoir where the temperature and pressure 350 K and 250 kPa, are respectively. At a certain point along the duct, where the cross-sectional area is 0.005 m, the pressure is 150 kPa. Determine the Mach number, temperature and velocity at that point and also calculate the mass flow rate. (Ans: 330.1 K, 0.549, 162.8 kPa, 1.718 kg-s*).

1. Air is flowing isentropically through a converging duct which is fed from a large reservoir where the temperature and pressure 350 K and 250 kPa, are respectively. At a certain point along the duct, where the cross-sectional area is 0.005 m, the pressure is 150 kPa. Determine the Mach number, temperature and velocity at that point and also calculate the mass flow rate. (Ans: 330.1 K, 0.549, 162.8 kPa, 1.718 kg-s*).

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

Carbon dioxide flows steadily through a varying cross-sectional area duct such as a nozzle shown in fig at a mass flow rate of 3.00 kg/s. The carbon dioxide enters the duct at a pressure of 1400 kPa and 200°C with a low velocity, and it expands in the nozzle to an exit 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 an overall pressure drop of 200 kPa.
Compressed air from the compressor of a gas turbine enters the combustion chamber at T1 = 700 K, P1 = 600 kPa, and Ma1 = 0.2 at a rate of 0.3 kg/s. Via combustion, heat is transferred to the air at a rate of 150 kJ/s as it flows through the duct with negligible friction. Determine the Mach number at the duct exit, and the drop in stagnation pressure P01 − P02 during this process
A converging duct is fed with air from a large reservoir where the temperature and pressure are 400 K and 200 kPa, respectively. The Mach number at a point along the duct, where the cross•sectional area is 0.01 m', is 0.7. Determine the temperature, pressure, velocity and density at that point, and also calculate the mass flow rate. Assume lsentropic flow throughout the nozzle.
Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.6. If the pressure and temperature of air are 58 kPa and 270 K, respectively, upstream of the shock, calculate the pressure, temperature velocity, Mach number, and stagnation pressure downstream of the shock. Calculate the entropy changes of air and helium across the normal shock wave
Air flows with negligible friction through a 6-in-diameter duct at a rate of 9 lbm/s. The temperature and pressure at the inlet are T1 = 800 R and P1 = 30 psia, and the Mach number at the exit is Ma2 = 1. Determine the rate of heat transfer and the pressure drop for this section of the duct.
6 A converging nozzle Is fed with air from a large reservoir where the . temperature and pressure are 400 K and 170 kPa, respectively. The nozzle has an exit cross-sectional area of 0.001 m2 and discharges into the atmosphere with a pressure of 100 kPa. The flow Is isentropic throughout the nozzle. Determine the pressure, Mach number, temperature and velocity at the exit plane, and also /ind the mass flow rate.
Carbon dioxide enters an adiabatic nozzle at 1200 K with a velocity of 50 m/s and leaves at 400 K. Assuming constant specific heats at room temperature, determine the Mach number (a) at the inlet and (b) at the exit of the nozzle. Assess the accuracy of the constant specific heat approximation.
Air flows isentropically through a duct. At section 1, thepressure and temperature are 250 kPa and 125°C, andthe velocity is 200 m/s. At section 2, the area is 0.25 m2 andthe Mach number is 2.0. Determine (a) Ma1; (b) T2; (c) V2;and (d ) the mass fl ow.
Air enters the diffuser with a velocity of 196 m/s. Determine the flow Mach number at the diffuser inlet when the air temperature is 30 Co. Use R=287 J/kgK and k=1.4. Please keep one decimal for the final answer.
1)Air is supplied to a converging nozzle from a large reservoir where the temperature and pressure are 400 Kand 150 kPa, respectively. At a certain cross-section where the area Is 0.01 m2, the pressure and velocity are 100 kPa and 120 ms·', respectively. Assuming adiabatic flow, find the Mach number at this cross-section and determine the mass flow rate. 2) Helium flows adiabatically through a duct. At some section, where the area is 0.02 m2, the velocity is 500 ms·1 and the pressure is 100 kPa. Find the Mach number at the given section, and determine the mass flow rate if the stagnation temperature is 300 K
Air flowing at 8 psia, 480 R, and Ma1 = 2.0 is forced to undergo a compression turn of 15°. Determine the Mach number, pressure, and temperature of the air after the compression.
B) Does the Mach number of a gas flowing at a constant speed remain constant?