Thermodynamics: An Engineering Approach
9th Edition
ISBN: 9781259822674
Author: Yunus A. Cengel Dr., Michael A. Boles
Publisher: McGraw-Hill Education
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Chapter 17.7, Problem 19P
To determine
The inlet Mach number of the heat exchanger.
The outlet Mach number of the heat exchanger.
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N2 enters a steady-flow heat exchanger at 150 kPa, 10°C, and 100 m/s, and it receives heat in the amount of 120 k/kg as it flows through it. The gas leaves the heat exchanger at 100 kPa with a velocity of 200 m/s. Determine the Mach number of the nitrogen at the inlet and the exit of the heat exchanger.
The Airbus A-340 passenger plane has a maximum takeoff weight of about 260,000 kg, a length of 64 m, a wing span of 60 m, a maximum cruising speed of 945 km/h, a seating capacity of 271 passengers, a maximum cruising altitude of 14,000 m, and a maximum range of 12,000 km. The air temperature at the crusing altitude is about −60°C. Determine the Mach number of this plane for the stated limiting conditions.
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.
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
Ch. 17.7 - Prob. 11PCh. 17.7 - Prob. 12PCh. 17.7 - Prob. 13PCh. 17.7 - Prob. 14PCh. 17.7 - Prob. 15PCh. 17.7 - Prob. 16PCh. 17.7 - Prob. 17PCh. 17.7 - Prob. 18PCh. 17.7 - Prob. 19PCh. 17.7 - Prob. 20PCh. 17.7 - Prob. 21PCh. 17.7 - Prob. 22PCh. 17.7 - Prob. 23PCh. 17.7 - Prob. 24PCh. 17.7 - Prob. 25PCh. 17.7 - Prob. 26PCh. 17.7 - The isentropic process for an ideal gas is...Ch. 17.7 - Is it possible to accelerate a gas to a supersonic...Ch. 17.7 - Prob. 29PCh. 17.7 - Prob. 30PCh. 17.7 - A gas initially at a supersonic velocity enters an...Ch. 17.7 - Prob. 32PCh. 17.7 - Prob. 33PCh. 17.7 - Prob. 34PCh. 17.7 - Prob. 35PCh. 17.7 - Prob. 36PCh. 17.7 - Prob. 37PCh. 17.7 - Air at 25 psia, 320F, and Mach number Ma = 0.7...Ch. 17.7 - Prob. 39PCh. 17.7 - Prob. 40PCh. 17.7 - Prob. 41PCh. 17.7 - Prob. 42PCh. 17.7 - Prob. 43PCh. 17.7 - Is it possible to accelerate a fluid to supersonic...Ch. 17.7 - Prob. 45PCh. 17.7 - Prob. 46PCh. 17.7 - Prob. 47PCh. 17.7 - Consider subsonic flow in a converging nozzle with...Ch. 17.7 - Consider a converging nozzle and a...Ch. 17.7 - Prob. 50PCh. 17.7 - Prob. 51PCh. 17.7 - Prob. 52PCh. 17.7 - Prob. 53PCh. 17.7 - Prob. 54PCh. 17.7 - Prob. 57PCh. 17.7 - Prob. 58PCh. 17.7 - Prob. 59PCh. 17.7 - Prob. 60PCh. 17.7 - Prob. 61PCh. 17.7 - Air enters a nozzle at 0.5 MPa, 420 K, and a...Ch. 17.7 - Prob. 63PCh. 17.7 - Are the isentropic relations of ideal gases...Ch. 17.7 - What do the states on the Fanno line and the...Ch. 17.7 - It is claimed that an oblique shock can be...Ch. 17.7 - Prob. 69PCh. 17.7 - Prob. 70PCh. 17.7 - For an oblique shock to occur, does the upstream...Ch. 17.7 - Prob. 72PCh. 17.7 - Prob. 73PCh. 17.7 - Prob. 74PCh. 17.7 - Prob. 75PCh. 17.7 - Prob. 76PCh. 17.7 - Prob. 77PCh. 17.7 - Prob. 78PCh. 17.7 - Prob. 79PCh. 17.7 - Air flowing steadily in a nozzle experiences a...Ch. 17.7 - Air enters a convergingdiverging nozzle of a...Ch. 17.7 - Prob. 84PCh. 17.7 - Prob. 85PCh. 17.7 - Consider the supersonic flow of air at upstream...Ch. 17.7 - Prob. 87PCh. 17.7 - Prob. 88PCh. 17.7 - Air flowing at 40 kPa, 210 K, and a Mach number of...Ch. 17.7 - Prob. 90PCh. 17.7 - Prob. 91PCh. 17.7 - Prob. 92PCh. 17.7 - What is the characteristic aspect of Rayleigh...Ch. 17.7 - Prob. 94PCh. 17.7 - Prob. 95PCh. 17.7 - What is the effect of heat gain and heat loss on...Ch. 17.7 - Consider subsonic Rayleigh flow of air with a Mach...Ch. 17.7 - Prob. 98PCh. 17.7 - Prob. 99PCh. 17.7 - Air is heated as it flows subsonically through a...Ch. 17.7 - Prob. 101PCh. 17.7 - Prob. 102PCh. 17.7 - Prob. 103PCh. 17.7 - Air enters a rectangular duct at T1 = 300 K, P1 =...Ch. 17.7 - Prob. 106PCh. 17.7 - Prob. 107PCh. 17.7 - Air is heated as it flows through a 6 in 6 in...Ch. 17.7 - What is supersaturation? Under what conditions...Ch. 17.7 - Steam enters a converging nozzle at 5.0 MPa and...Ch. 17.7 - Steam enters a convergingdiverging nozzle at 1 MPa...Ch. 17.7 - Prob. 112PCh. 17.7 - Prob. 113RPCh. 17.7 - Prob. 114RPCh. 17.7 - Prob. 115RPCh. 17.7 - Prob. 116RPCh. 17.7 - Prob. 118RPCh. 17.7 - Prob. 119RPCh. 17.7 - Using Eqs. 174, 1713, and 1714, verify that for...Ch. 17.7 - Prob. 121RPCh. 17.7 - Prob. 122RPCh. 17.7 - Prob. 123RPCh. 17.7 - Prob. 124RPCh. 17.7 - Prob. 125RPCh. 17.7 - Prob. 126RPCh. 17.7 - Nitrogen enters a convergingdiverging nozzle at...Ch. 17.7 - An aircraft flies with a Mach number Ma1 = 0.9 at...Ch. 17.7 - Prob. 129RPCh. 17.7 - Helium expands in a nozzle from 220 psia, 740 R,...Ch. 17.7 - Helium expands in a nozzle from 0.8 MPa, 500 K,...Ch. 17.7 - Air is heated as it flows subsonically through a...Ch. 17.7 - Air is heated as it flows subsonically through a...Ch. 17.7 - Prob. 134RPCh. 17.7 - Prob. 135RPCh. 17.7 - Air is cooled as it flows through a 30-cm-diameter...Ch. 17.7 - Saturated steam enters a convergingdiverging...Ch. 17.7 - Prob. 138RPCh. 17.7 - Prob. 145FEPCh. 17.7 - Prob. 146FEPCh. 17.7 - Prob. 147FEPCh. 17.7 - Prob. 148FEPCh. 17.7 - Prob. 149FEPCh. 17.7 - Prob. 150FEPCh. 17.7 - Prob. 151FEPCh. 17.7 - Prob. 152FEPCh. 17.7 - Consider gas flow through a convergingdiverging...Ch. 17.7 - Combustion gases with k = 1.33 enter a converging...
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- Nitrogen enters a steady-flow heat exchanger at 150 kPa, 10°C, and 100 m/s, and it receives heat in the amount of 150 kJ/kg as it flows through it. The nitrogen leaves the heat exchanger at 100 kPa with a velocity of 200 m/s. Determine the stagnation pressure and temperature of the nitrogen at the inlet and exit states.arrow_forwardFor the specific volume of wet steam, SV=(1-Xv)SV (liq) + XvSV (vapor). Entropy is also calculated this way. If a tank initially has 5kg of wet steam with mass of vapor =1 kg at 100 kPa, and it is heated such that saturated vapor remains in the tank. Assuming that the process is in constant volume, what will be the entropy change of the steam (Kj/K)?arrow_forwardThe fluid is heated from 125 degrees Fahrenheit to 225 degrees Fahrenheit. Consider an ideal gas with the following characteristics: R = 85 ft-lbf/lbm-R Cp = 0.35 + 0.000325T BTU/lbm-R If the heating is at constant volume, compute for (a) the change in internal energy, (b) the change in enthalpy, and (c) the change in entropy. If the heating is at constant pressure, compute for (d) the change in entropy, and (e) the value of k at 160 degrees Celsius. If the fluid undergoes an isentropic process, determine (f) non-flow work and (g) steady-flow work. (For item f and g, use the value of k at 160 degrees Celsius). Note: The unit should be in metric system. Should have given, required and the solution.arrow_forward
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