- 12.29P: What would happen if we tried to further accelerate a supersonic fl...
- 12.31P: Consider subsonic flow in a converging nozzle with specified condit...
- 12.32P: Consider a converging nozzle and a converging – diverging nozzle ha...
- 12.33P: Consider gas flow through a converging nozzle with specified inlet ...
- 12.34P: How does the parameter Ma* differ from the Mach number Ma?
- 12.35P : Consider the isentropic flow of a fluid through a converging – dive...
- 12.36P: Is it possible to accelerate a fluid to supersonic velocities with ...
- 12.37P: Explain why the maximum flow rate per unit area for a given ideal g...
- 12.38P: For an ideal gas obtain an expression for the ratio of the speed of...
- 12.39P: Air enters a converging–diverging nozzle at 1.2 MPa with a negligib...
- 12.40P: Air enters a nozzle at 0.6 MPa, 420 K, and a velocity of 150 m/s. A...
- 12.41P: Repeat Prob. 12–42 assuming the entrance velocity is negligible.
- 12.42P: An ideal gas flows through a passage that first converges and then ...
- 12.43P: Repeat Prob. 12–45 for supersonic flow at the inlet.
- 12.44P: Nitrogen enters a converging–diverging nozzle at 700 kPa and 400 K ...
- 12.45P: An ideal gas with k = 1.4 isflowing through a nozzle such that the ...
- 12.46P: Repeat Prob. 12–48 for an ideal gas with k = 1.33.
- 12.48P: Air at 900 kPa and 400 K enters a converging nozzle with a negligib...
- 12.49P: Reconsider Prob. 12–51. Using EES (or other) software, solve the pr...
- 12.54P: Can a shock wave develop in the converging section of a converging–...
- 12.56P: Can the Mach number of a fluid be greater than 1 after a normal sho...
- 12.55P: What do the states on the Fanno line and the Rayleigh line represen...
- 12.57P: How does the normal shock affect (a) the fluid velocity,(b) the sta...
- 12.58P: How do oblique shocks occur? How do oblique shocks differ from norm...
- 12.59P: For an oblique shock to occur, does the upstream flow have to be su...
- 12.60P: It is claimed that an oblique shock can be analyzed like a normal s...
- 12.61P: Consider supersonic airflow approaching the nose of a two-dimension...
- 12.62P: Consider supersonic flow impinging on the rounded nose of an aircra...
- 12.64P: Air enters, a normal shock at 18 kPa, 205 K, and 740 m/s. Calculate...
- 12.63P: Are the isentropic relations of ideal gases applicable for flows ac...
- 12.65P: Calculate the entropy change of air across the normal shock wave in...
- 12.66P: Air enters a converging–diverging nozzle of a supersonic wind tunne...
- 12.67P: Air enters a converging–diverging nozzle with low velocity at 2.0 M...
- 12.68P: What must the back pressure be in Prob. 12–70 for a normal shock to...
- 12.69P: Air flowing steadily in a nozzle experiences a normal shock at a Ma...
- 12.70P: Calculate the entropy change of air across the normal shock wave in...
- 12.71P: For an ideal gas flowing through a normal shock, develop a relation...
- 12.72P: Using EES (or other) software, calculate and plot the entropy chang...
- 12.73P: Consider supersonic airflow approaching the nose of a two-dimension...
- 12.75P: Consider the supersonic flow of air at upstream conditions of 70 kP...
- 12.76P: Reconsider Prob. 12–80. Determine the downstream Mach number, press...
- 12.78P: Air flowing at 40 kPa, 280 K, and Ma1, = 3.6 is forced to undergo a...
- 12.77P: Air at 12 psia, 30°F, and a Mach number of 2.0 is forced to turn up...
- 12.79P: Air flowing at 60 kPa, 240 K, and a Mach number of 3.4 impinges on ...
- 12.84P: What is the characteristic aspect of Rayleigh flow? What are the ma...
- 12.85P: On a T-s diagram of Rayleigh flow, what do the points on the Raylei...
- 12.86P: What is the effect of heat gain and heat loss on the entropy of the...
- 12.87P: Consider subsonic Rayleigh flow of air with a Mach number of 0.92. ...
- 12.88P: What is the effect of heating the fluid on the flow velocity in sub...
- 12.89P: Consider subsonic Rayleigh flow that is accelerated to sonic veloci...
- 12.90P: Consider a 16-cm-diaineter tubular, combustion chamber. Air enters ...
- 12.91P: Air is heated as it flows subsonjcally through a duct. When the amo...
- 12.93P: Air enters an approximately frictionless duct with V1 = 70 m/s, T1 ...
- 12.95P: Compressed air from the compressor of a gas turbine enters the comb...
- 12.96P: Repeat Prob. 12–100 for a heat transfer rate of 300 kJ/s.
- 12.97P: Air enters a rectangular duct at T1 = 300 K, P1 = 420 kPa, and Ma1 ...
- 12.98P: Repeat Prob. 12–102 assuming air is cooled in the amount of 55 kJ/kg.
- 12.99P: Argon gas enters a constant cross-sectional area duct at Ma1 = 0.2,...
- 12.100P: Consider supersonic flow of air through a 10-cm diameter duct with ...
- 12.101P: What is the characteristic aspect of Fanno flow? What are the main ...
- 12.102P: On a T-s diagram of Fanno flow, what do the points on the Fanno lin...
- 12.103P: What is the effect of friction on the entropy of the fluid during F...
- 12.104P: Consider subsonic Fanno flow of air with an inlet Mach number of 0....
- 12.105P: Consider supersonic Fanno flow of air with an inlet Mach number of ...
- 12.106P: What is the effect of friction on flow velocity in subsonic Fanno f...
- 12.107P: Consider subsonic Fanno flow accelerated to sonic velocity (Ma = 1)...
- 12.108P: Consider supersonic Fanno flow that is decelerated to sonic velocit...
- 12.109P: Air enters a 15-cm-diameter adiabatic duct with inlet conditions of...
- 12.110P: Air enters a 15-m-long, 4-cm-diameter adiabatic duct at V1 = 70 m/s...
- 12.111P: Air in a room at T0 = 300 K and P0 = 100 kPa is drawn steadily by a...
- 12.112P: Repeat Prob. 12–116 for a friction factor of 0.025 and a tube lengt...
- 12.113P: Air enters a 5-cm-diameter, 4-m-long adiabatic duct with inlet cond...
- 12.115P: Air enters a 5-cm-diameter adiabatic duct at Ma1 = 0.4, T1 = 550 K,...
- 12.116P: Consider subsonic airflow through a 20 cm diameter adiabatic duct w...
- 12.118P: Argon gas with k = 1.667, and cp= 0.5203 kJ/kg K, R = 0.2081 kJ/kg·...
- 12.117P: Repeat Prob. 12–122 for helium gas.
- 12.120P: Nitrogen enters a ductwith varying flow area at 400 K, 100 kPa, and...
- 12.122P: The thrust developed by the engine of a Boeing 777 is about 380 kN....
- 12.123P: A stationary temperature probe inserted into a duct where air is fl...
- 12.124P: Nitrogen enters a steady-flow heat exchanger at 150 kPa, 10°C, and ...
- 12.125P: Derive an expression for the speed of sound based on van der Waals’...
- 12.126P: Obtain Eq: 12–10 by starting with Eq. 12–9 and using the cyclic rul...
- 12.127P: For ideal gases undergoing isentropie flows, obtain expressions for...
- 12.128P: Using Eqs. 12–4, 12–13, and 12–14, verify that for the steady flow ...
- 12.129P: A subsonic airplane is flying at a 5000-m altitude where the atmosp...
- 12.130P: Plot the mass flow parameter versus the Mach number fork =1.2, 1.4,...
- 12.131P: Helium enters a nozzle at 0.6 MPa, 560 K, and a velocity of 120 m/s...
- 12.132P: Repeat 12–137 assuming the entrance velocity is negligible.
- 12.2P: What is dynamic temperature?
- 12.134P: Nitrogen enters a converging–diverging nozzle at 620 kPa and 310 K ...
- 12.135P: An aircraft flies with a Mach number Ma1 = 0.8 at an altitude of 70...
- 12.136P: Helium expands in a nozzle from 1 MPa, 500 K, and negligible veloci...
- 12.137P: Using the EES software and the relations in Table A-13, calculate t...
- 12.138P: Using the EES software and the relations in Table A–14, calculate t...
- 12.139P: Consider an equimolar mixture of oxygen and nitrogen. Determine the...
- 12.140P: In compressible flow, velocity measurements with a Pitot probe can ...
- 12.141P: Using EES (or other) software and the relations given in Table A–13...
- 12.142P: Repeat Prob. 12–148 for methane with k =1.3.
- 12.143P: Using EES (or other) software and the relations given in Table A–14...
- 12.144P: Repeat Prob. 12–150 for methene with k = 1.3.
- 12.146P: Air enters a 4-cm-diametcr adiabatic duct with inlet conditions of ...
- 12.147P: Air is cooled as it flows through a 20-cm-diameter duct. The inlet ...
- 12.148P: Air is heated as it flows subsonically through a 10 cm × 10 cm squa...
- 12.149P: Repeat Prob. 12–155 for helium.
- 12.150P: Air is accelerated as it is heated in a duct with negligible fricti...
- 12.151P: Air at sonic conditions and at static temperature and pressure of 4...
- 12.152P: Combustion gases with an ave rage spec ific heat ratio of k= 1.33 a...
- 12.153P: Consider supersonic airflow through a 12-cm- diameter adiabatic duc...
- 12.154P: Air is flowing through a 6-cm diameter adiabatic duct with inlet co...
- 12.157P: Find the expression for the ratio of the stagnation pressure after ...
- 12.1P: How and why is the stagnation enthalpy h0 defined? How does it diff...
- 12.3P: A high-speed aircraft is cruising in still air How does the tempera...
- 12.4P: Air enters a compressor with a stagnation pressure of l00 kPa and a...
- 12.5P: Air at 320 K is flowing in a duct at a velocity of (a) 1, (b) 10, (...
- 12.6P: Calculate the stagnation temperature and pressure for the following...
- 12.7P: Determine the stagnation temperature and stagnation pressure of air...
- 12.8P: Steam flows through a device with a stagnation pressure of 120 psia...
- 12.9P: Air flows through a device such that the stagnation pressure is 0.6...
- 12.10P: Products of combustion enter a gas turbine with a stagnation pressu...
- 12.11P: A gas initially at a subsonic velocity enters an adiabatic convergi...
- 12.12P: A gas initially at a subsonic velocity enters an adiabatic divergin...
- 12.13P: Consider a converging nozzle with sonic speed at the exit plane. No...
- 12.14P: A gas initially at a supersonic velocity enters an adiabatic conver...
- 12.15P: A gas initially at a supersonic velocity enters an adiabatic diverg...
- 12.16P: A gas at a specified stagnation temperature and pressure is acceler...
- 12.17P: Is it possible to accelerate a gas to a supersonic velocity in a co...
- 12.18P: In March 2004, NASA successfully launched an experimental supersoni...
- 12.19P: Reconsider the scram jet engine discussed in Prob. 12–19. Determine...
- 12.20P: Consider a large commercial airplane cruising at a speed of 920 km/...
- 12.21P: Calculate the critical temperature, pressure, and density of (a) ai...
- 12.22P: Quiescent carbon dioxide at 1200 kPa and 600 K is accelerated isent...
- 12.23P: Air enters a converging–diverging nozzle at a pressure of 800 kPa w...
- 12.24P: Helium enters a converging–diverging nozzle at 0.7 MPa, 800 K, and ...
- 12.25P: Air at 200 kPa, 100°C, and Mach number Ma = 0.8 flows through a duc...
- 12.26P: Reconsider Prob. 12–26. Using EES (or other) software, study the ef...
- 12.27P: An aircraft is designed to cruise at Mach number Ma = 1.4 at 8000 m...
- 12.28P: What would happen if we attempted to decelerate a supersonic fluid ...
- 12.30P: Consider subsonic flow in a converging nozzle with fixed inlet cond...

# Solutions for Chapter 12: Fluid Mechanics 2nd Edition

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ISBN: 9780071284219

Solutions for Chapter 12

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