- 17.1P: A high-speed aircraft is cruising in still air. How does the temper...
- 17.2P: What is dynamic temperature?
- 17.3P: In air-conditioning applications, the temperature of air is measure...
- 17.4P: Air flows through a device such that the stagnation pressure is 0.6...
- 17.5P: Air at 320 K is flowing in a duct at a velocity of (a) 1, (b) 10, (...
- 17.6P: Calculate the stagnation temperature and pressure for the following...
- 17.7P: Determine the stagnation temperature and stagnation pressure of air...
- 17.8P: Steam flows through a device with a stagnation pressure of 120 psia...
- 17.9P: Air enters a compressor with a stagnation pressure of 100 kPa and a...
- 17.10P: Products of combustion enter a gas turbine with a stagnation pressu...
- 17.11P: What is sound? How is it generated? How does it travel? Can sound w...
- 17.12P: In which medium does a sound wave travel faster: in cool air or in ...
- 17.13P: In which medium will sound travel fastest for a given temperature: ...
- 17.14P: In which medium does a sound wave travel faster: in air at 20°C and...
- 17.15P: Does the Mach number of a gas flowing at a constant velocity remain...
- 17.16P: Is it realistic to assume that the propagation of sound waves is an...
- 17.17P: Is the sonic velocity in a specified medium a fixed quantity, or do...
- 17.18P: The Airbus A-340 passenger plane has a maximum takeoff weight of ab...
- 17.19P: Carbon dioxide enters an adiabatic nozzle at 1200 K with a velocity...
- 17.20P: Nitrogen enters a steady-flow heat exchanger at 150 kPa, 10°C, and ...
- 17.21P: Assuming ideal gas behavior, determine the speed of sound in refrig...
- 17.22P: Determine the speed of sound in air at (a) 300 K and (b) 1000 K. Al...
- 17.23P: Steam flows through a device with a pressure of 120 psia, a tempera...
- 17.25P: Air expands isentropicahy from 170 psia and 200°F to 60 psia. Calcu...
- 17.26P: Air expands isentropically from 2.2 MPa and 77°C to 0.4 MPa. Calcul...
- 17.27P: Repeat Prob. 17–26 for helium gas. 17–26Air expands isentropically ...
- 17.28P: The isentropic process for an ideal gas is expressed as PVk=constan...
- 17.29P: Is it possible to accelerate a gas to a supersonic velocity in a co...
- 17.30P: A gas initially at a subsonic velocity enters an adiabatic divergin...
- 17.31P: A gas at a specified stagnation temperature and pressure is acceler...
- 17.32P: A gas initially at a supersonic velocity enters an adiabatic conver...
- 17.33P: A gas initially at a supersonic velocity enters an adiabatic diverg...
- 17.34P: Consider a converging nozzle with sonic speed at the exit plane. No...
- 17.35P: A gas initially at a subsonic velocity enters an adiabatic convergi...
- 17.36P: Helium enters a converging–diverging nozzle at 0.7 MPa, 800 K, and ...
- 17.37P: Consider a large commercial airplane cruising at a speed of 920 km/...
- 17.38P: Calculate the critical temperature, pressure, and density of (a) ai...
- 17.39P: Air at 25 psia, 320°F, and Mach number Ma = 0.7 flows through a duc...
- 17.40P: Air enters a converging-diverging nozzle at a pressure of 1200 kPa ...
- 17.41P: In March 2004, NASA successfully launched an experimental supersoni...
- 17.42P: Reconsider the scram jet engine discussed in Prob. 17–37. Determine...
- 17.43P: Air at 200 kPa, 100°C, and Mach number Ma = 0.8 flows through a duc...
- 17.45P: An aircraft is designed to cruise at Mach number Ma = 1.1 at 12,000...
- 17.46P: Quiescent carbon dioxide at 1200 kPa and 600 K is accelerated isent...
- 17.47P: Is it possible to accelerate a fluid to supersonic velocities with ...
- 17.49P: How does the parameter Ma* differ from the Mach number Ma?
- 17.50P: Consider subsonic flow in a converging nozzle with specified condit...
- 17.51P: Consider a converging nozzle and a converging–diverging nozzle havi...
- 17.52P: Consider gas flow through a converging nozzle with specified inlet ...
- 17.53P: Consider subsonic flow in a converging nozzle with fixed inlet cond...
- 17.54P: Consider the isentropic flow of a fluid through a converging–diverg...
- 17.55P: What would happen if we attempted to decelerate a supersonic fluid ...
- 17.56P: Nitrogen enters a converging-diverging nozzle at 700 kPa and 400 K ...
- 17.57P: For an ideal gas obtain an expression for the ratio of the speed of...
- 17.58P: Air enters a converging–diverging nozzle at 1.2 MPa with a negligib...
- 17.59P: Air enters a nozzle at 30 psia, 630 R, and a velocity of 450 ft/s. ...
- 17.60P: An ideal gas flows through a passage that first converges and then ...
- 17.61P: Repeat Prob. 17–63 for supersonic flow at the inlet.
- 17.62P: Explain why the maximum flow. rate, per unit area for a given ideal...
- 17.63P: An ideal gas with k = 1.4 is flowing through a nozzle such that the...
- 17.64P: Repeat Prob. 17–63 for an ideal gas with k = 1.33. 17–63An ideal ga...
- 17.65P: Air enters a converging–diverging nozzle of a supersonic wind tunne...
- 17.66P: Air enters a nozzle at 0.5 MPa, 420 K, and a velocity of 110 m/s. A...
- 17.67P: Repeat Prob. 17–66 assuming the entrance velocity is negligible. 17...
- 17.70P: Repeat Prob. 17–66 assuming the entrance velocity is negligible. 17...
- 17.71P: What do the states on the Fanno line and the Rayleigh line represen...
- 17.72P: It is claimed that an oblique shock can be analyzed like a normal-s...
- 17.73P: How does the normal shock affect (a) the fluid velocity, (b) the st...
- 17.74P: How do oblique shocks occur? How do oblique shocks differ from norm...
- 17.75P: For an oblique shock to occur, does the upstream flow have to be su...
- 17.76P: Can the Mach number of a fluid be greater than 1after a normal shoc...
- 17.77P: Consider supersonic airflow approaching the nose of a two-dimension...
- 17.78P: Consider supersonic flow impinging on the rounded nose of an aircra...
- 17.79P: Can a shock wave develop in the converging section of a converging–...
- 17.80P: Air enters a normal shock at 26 kPa, 230 K, and 815 m/s. Calculate ...
- 17.81P: Calculate the entropy change of air across the normal shock wave in...
- 17.82P: For an ideal gas flowing through a normal shock, develop a relation...
- 17.83P: Air enters a converging–diverging nozzle with low velocity at 2.0 M...
- 17.84P: What must the back pressure be in Prob. 17–84 for a normal shock to...
- 17.85P: Air flowing steadily in a nozzle experiences a normal shock at a Ma...
- 17.87P: Air enters a converging–diverging nozzle of a supersonic wind tunne...
- 17.89P: Consider supersonic airflow approaching the nose of a two-dimension...
- 17.90P: Air flowing at 32 kPa, 240 K, and Ma1 = 3.6 is forced to undergo an...
- 17.91P: Consider the supersonic flow of air at upstream conditions of 70 kP...
- 17.92P: Reconsider Prob. 17–94. Determine the downstream Mach number, press...
- 17.95P: Air flowing at 60 kPa, 240 K, and a Mach number of 3.4 impinges on ...
- 17.96P: Air flowing steadily in a nozzle experiences a normal shock at a Ma...
- 17.97P: Calculate the entropy changes of air and helium across the normal s...
- 17.98P: What is the effect of heating the fluid on the flow velocity in sub...
- 17.99P: On a T-sdiagram of Rayleigh flow, what do the points on the Rayleig...
- 17.100P: What is the effect of heat gain and heat loss on the entropy of the...
- 17.101P: Consider subsonic Rayleigh flow of air with a Mach number of 0.92. ...
- 17.102P: What is the effect of heating the fluid on the flow velocity in sub...
- 17.103P: Consider subsonic Rayleigh flow that is accelerated to sonic veloci...
- 17.104P: Argon gas enters a constant cross-sectional area duct at Ma1 = 0.2,...
- 17.105P: Air is heated as it flows subsonically through a duct. When the amo...
- 17.106P: Compressed air from the compressor of a gas turbine enters the comb...
- 17.107P: Repeat Prob. 17–106 for a heat transfer rate of 300 kJ/s. 17–106Com...
- 17.108P: Air flows with negligible friction through a 4-in-diameter duct at ...
- 17.110P: Air is heated as it flows through a 6 in × 6 in square duct with ne...
- 17.111P: Air enters a rectangular duct at T1 = 300 K, P1 = 420 kPa, and Ma1 ...
- 17.112P: Repeat Prob. 17–112 assuming air is cooled in the amount of 55 kJ/kg.
- 17.113P: Consider a 16-cm-diameter tubular combustion chamber. Air enters th...
- 17.115P: What is supersaturation? Under what conditions does it occur?
- 17.116P: Steam enters a converging nozzle at 5.0 MPa and 400°C with a neglig...
- 17.117P: Steam enters a converging nozzle at 450 psia and 900°F with a negli...
- 17.118P: Steam enters a converging–diverging nozzle at 1 MPa and 500°C with ...
- 17.119P: Repeat Prob. 17–118 for a nozzle efficiency of 85 percent. 17–118St...
- 17.120P: The thrust developed by the engine of a Boeing 777 is about 380 kN....
- 17.121P: A stationary temperature probe inserted into a duct where air is fl...
- 17.122P: Nitrogen enters a steady-flow heat exchanger at 150 kPa, 10°C, and ...
- 17.123P: Plot the mass flow parameter versus the Mach number for k=1.2,1.4, ...
- 17.124P: Obtain Eq. 17–10 by starting with Eq. 17–9 and using the cyclic rul...
- 17.125P: For ideal gases undergoing isentropic flows, obtain expressions for...
- 17.126P: Using Eqs. 17–4,17-13, and 17–14, verify that for the steady flow o...
- 17.127P: A subsonic airplane is flying at a 5000-m altitude where the atmosp...
- 17.128P: Derive an expression for the speed of sound based on van der Waals'...
- 17.129P: Helium enters a nozzle at 0.6 MPa, 560 K, and a velocity of 120 m/s...
- 17.130P: Repeat 17–129 assuming the entrance velocity is negligible. 17–129H...
- 17.132P: Nitrogen enters a duct with varying flow area at 400 K, 100 kPa, an...
- 17.133P: Repeat Prob. 17–132 for an inlet Mach number of 0.5. 17–132Nitrogen...
- 17.134P: Nitrogen enters a converging-diverging nozzle at 620 kPa and 310 K ...
- 17.135P: An aircraft flies with a Mach number Ma1 = 0.9 at an altitude of 70...
- 17.136P: Consider an equimolar mixture of oxygen and nitrogen. Determine the...
- 17.137P: Helium expands in a nozzle from 220 psia, 740 R, and negligible vel...
- 17.140P: Helium expands in a nozzle from 1 MPa, 500 K, and negligible veloci...
- 17.143P: Air is heated as it flows subsonically through a 10 cm × 10 cm squa...
- 17.144P: Repeat Prob. 17–143 for helium. 17–143Air is heated as it flows sub...
- 17.145P: Air is accelerated as it is heated in a duct with negligible fricti...
- 17.146P: Air at sonic conditions and at static temperature and pressure of 3...
- 17.147P: Air is cooled as it flows through a 20-cm-diameter duct. The inlet ...
- 17.148P: Saturated steam enters a converging–diverging nozzle at 1.75 MPa, 1...
- 17.151P: Find the expression for the ratio of the stagnation pressure after ...
- 17.154P: An aircraft is cruising in still air at 5°C at a velocity of 400 m/...
- 17.155P: Air is flowing in a wind tunnel at 25°C, 80 kPa, and 250 m/s. The s...
- 17.156P: An aircraft is reported to be cruising in still air at –20°C and 40...
- 17.157P: ?roblem 157PAir is flowing in a wind tunnel at 12°C and 66 kPa at a...
- 17.158P: Consider a converging nozzle with a low velocity at the inlet and s...
- 17.159P: Air is approaching a converging–diverging nozzle with a low velocit...
- 17.160P: Argon gas is approaching a converging–diverging nozzle with a low v...
- 17.161P: Carbon dioxide enters a converging–diverging nozzle at 60 m/s, 310°...
- 17.162P: Consider gas flow through a converging–diverging nozzle. Of the fiv...
- 17.163P: Combustion gases with k =1.33 enter a converging nozzle at stagnati...

# Solutions for Chapter 17: Thermodynamics: An Engineering Approach 8th Edition

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ISBN: 9780073398174

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