Thermodynamics: An Engineering Approach
9th Edition
ISBN: 9781259822674
Author: Yunus A. Cengel Dr., Michael A. Boles
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 17.7, Problem 127RP
Nitrogen enters a converging–diverging nozzle at 620 kPa and 310 K with a negligible velocity, and it experiences a normal shock at a location where the Mach number is Ma = 3.0. Calculate the pressure, temperature, velocity, Mach number, and stagnation pressure downstream of the shock. Compare these results to those of air undergoing a normal shock at the same conditions.
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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. Compare these results to those for helium undergoing a normal shock under the same conditions.
Nitrogen enters a converging–diverging nozzle at 620 kPa and 310 K with a negligible velocity, and it experiences a normal shock at a location where the Mach number is Ma = 3.0. Calculate the pressure, temperature, velocity, Mach number, and stagnation pressure downstream of the shock. Compare these results to those of air undergoing a normal shock at the same conditions.
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Chapter 17 Solutions
Thermodynamics: An Engineering Approach
Ch. 17.7 - A high-speed aircraft is cruising in still air....Ch. 17.7 - What is dynamic temperature?Ch. 17.7 - Prob. 3PCh. 17.7 - Prob. 4PCh. 17.7 - Prob. 5PCh. 17.7 - Prob. 6PCh. 17.7 - Calculate the stagnation temperature and pressure...Ch. 17.7 - Prob. 8PCh. 17.7 - Prob. 9PCh. 17.7 - Prob. 10P
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- Nitrogen enters a duct with varying flow area at 400 K, 100 kPa, and a Mach number of 0.5. Assuming a steady, isentropic flow, determine the temperature, pressure, and Mach number at a location where the flow area has been reduced by 20 percent.arrow_forwardAn ideal gas flows through a passage that first converges and then diverges during an adiabatic, reversible, steady-flow process. For supersonic flow at the inlet, sketch the variation of pressure, velocity, and Mach number along the length of the nozzle when the Mach number at the minimum flow area is equal to unity.arrow_forwardNitrogen enters a converging–diverging nozzle at 700 kPa and 400 K with a negligible velocity. Determine the critical velocity, pressure, temperature, and density in the nozzle.arrow_forward
- An air stream with a Mach number of (3.04) a pressure of (302 kPa) and a temperature of (502 K) enters a diverging channel. If the ratio of the exit cross- sectional area to the inlet cross- sectional area is (3). Determine the back pressure which is necessary to produce a normal shock wave in the channel with a cross-sectional area equal to twice the inlet cross-sectional area. Assume steady, one-dimensional isentropic flow except through the normal shock wave. Ax=2Ai , Ae=3Aiarrow_forwardAn ideal isentropic nozzle is attached to an infinite reservoir that has stagnation conditions 3 MPa and 2250 K, and a constant specific heat of 1.2. If the nozzle's static exit pressure is 38.871 kPa, what is the exit static temperature? Also determine the nozzle's exit Mach number, stagnation pressure, and stagnation temperature.arrow_forwardAhead of the normal shock wave, the upstream pressure , temperature, and Mach number are 0.53 atm, 255 K, and 2.8, respectively. Determine the pressure downstream of the shock wave.arrow_forward
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- Consider the isentropic flow through a convergent-divergent nozzle with an exit-to-throat area ratio of 2.5. The reservoir pressure and temperature are 1 atm and 288 K, respectively. Calculate the Mach number, pressure, and temperature at both the throat and the exit for the cases where (a) the flow is supersonic at the exit and (b) the flow is subsonic throughout the entire nozzle except at the throat, where M = 1.arrow_forwardHow does the Mach number affect the behavior of compressible flow in a supersonic nozzle?arrow_forwardD5. A converging-diverging nozzle operates with air and subsonic flow at the inlet and supersonic flow at the outlet with no shacks inside the nozzle. Determine the mach number and static pressure at the outlet if the area of the outlet is 0.900 m2, the area of the throat is 0.490m2, and the stagnation pressure is 215 kPa.arrow_forward
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