- 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...
- 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 \(T_{1}=300 \mathrm{~K}, P_{1}=\)...
- 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 t...
- 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 \(\dot{m} \sqrt{R T_{0}} /\left(A P_{...
- 17.124P: ?Obtain Eq. 17-10 by starting with Eq. 17-9 and using the cyclic ru...
- 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 \mathrm{~cm}...
- 17.144P: ?Repeat Prob. 17–143 for helium.
- 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: Compressible Flow

## Full solutions for Thermodynamics: An Engineering Approach | 8th Edition

ISBN: 9780073398174

Solutions for Chapter 17: Compressible Flow

Get Full SolutionsSummary of Chapter 17: Compressible Flow

We start this chapter by introducing the concepts of stagnation state, speed of sound, and Mach number for compressible flows. The relationships between the static and stagnation fluid properties are developed for isentropic flows of ideal gases, and they are expressed as functions of specific-heat ratios and the Mach number.

This textbook survival guide was created for the textbook: Thermodynamics: An Engineering Approach , edition: 8. Thermodynamics: An Engineering Approach was written by and is associated to the ISBN: 9780073398174. This expansive textbook survival guide covers the following chapters and their solutions. Chapter 17: Compressible Flow includes 143 full step-by-step solutions. Since 143 problems in chapter 17: Compressible Flow have been answered, more than 439816 students have viewed full step-by-step solutions from this chapter.