Fluid Mechanics Fundamentals And Applications
3rd Edition
ISBN: 9780073380322
Author: Yunus Cengel, John Cimbala
Publisher: MCGRAW-HILL HIGHER EDUCATION
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Chapter 12, Problem 125P
To determine
The pressure and temperature at the instant where speed equals the speed of sound. Ratio of area.
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At a point in an airflow the pressure, temperature, and velocity are 1 atm, 320 K, and 1000 m/s. Calculate the total temperature and total pressure at this point.
The Mach number of an aircraft that travels with a speed of 260 m/s in air at 25° C
while it undergoes the compressibility effect will be:
(Use speed of sound in air at 0° C: 331 m/s)
Select one:
a. M = 0.69
b. M= 0.70
c. M= 0.75
Helium enters a converging–diverging nozzle at 0.7 MPa, 800 K, and 100 m/s. What are the lowest temperature and pressure that can be obtained at the throat of the nozzle?
Chapter 12 Solutions
Fluid Mechanics Fundamentals And Applications
Ch. 12 - What is dynamic temperature?Ch. 12 - Prob. 4PCh. 12 - Prob. 5PCh. 12 - Calculate the stagnation temperature and pressure...Ch. 12 - Prob. 7PCh. 12 - Prob. 8EPCh. 12 - Prob. 9PCh. 12 - Products of combustion enter a gas turbine with a...Ch. 12 - Is it possible to accelerate a gas to a supersonic...Ch. 12 - Prob. 18P
Ch. 12 - Prob. 28PCh. 12 - Prob. 39PCh. 12 - Prob. 41EPCh. 12 - Prob. 64PCh. 12 - Air enters a converging—diverging nozzle with low...Ch. 12 - Prob. 75EPCh. 12 - Prob. 76EPCh. 12 - Prob. 78PCh. 12 - Prob. 79PCh. 12 - Prob. 80CPCh. 12 - On a T-s diagram of Raleigh flow, what do the...Ch. 12 - What is the effect of heat gain and heat toss on...Ch. 12 - Prob. 83CPCh. 12 - Prob. 84CPCh. 12 - Prob. 85CPCh. 12 - Argon gas enters a constant cross-sectional area...Ch. 12 - Prob. 87PCh. 12 - Prob. 88PCh. 12 - Prob. 89PCh. 12 - Prob. 90EPCh. 12 - Prob. 92EPCh. 12 - Prob. 93PCh. 12 - Prob. 94PCh. 12 - Prob. 95PCh. 12 - Prob. 96PCh. 12 - Prob. 97CPCh. 12 - Prob. 98CPCh. 12 - Prob. 99CPCh. 12 - Prob. 100CPCh. 12 - Prob. 101CPCh. 12 - Prob. 102CPCh. 12 - Prob. 103CPCh. 12 - Prob. 104CPCh. 12 - Air enters a 12-cm-diameter adiabatic duct at...Ch. 12 - Air enters a 15-m-long, 4-cm-diameter adiabatic...Ch. 12 - Air enters a 5-cm-diameter, 4-m-long adiabatic...Ch. 12 - Helium gas with k=1.667 enters a 6-in-diameter...Ch. 12 - Air enters a 15-cm-diameter adiabatic duct with...Ch. 12 - Air flows through a 6-in-diameter, 50-ft-long...Ch. 12 - Air in a room at T0=300k and P0=100kPa is drawn...Ch. 12 - Prob. 115PCh. 12 - Prob. 116PCh. 12 - Prob. 117PCh. 12 - Prob. 118PCh. 12 - Prob. 119PCh. 12 - Prob. 120PCh. 12 - Prob. 121PCh. 12 - Prob. 122PCh. 12 - A subsonic airplane is flying at a 5000-m altitude...Ch. 12 - Prob. 124PCh. 12 - Prob. 125PCh. 12 - Prob. 126PCh. 12 - Prob. 128PCh. 12 - Prob. 129PCh. 12 - Prob. 130PCh. 12 - An aircraft flies with a Mach number Ma1=0.9 at an...Ch. 12 - Prob. 132PCh. 12 - Helium expands in a nozzle from 220 psia, 740 R,...Ch. 12 - Prob. 136PCh. 12 - Prob. 137PCh. 12 - Prob. 138PCh. 12 - Prob. 139PCh. 12 - Prob. 140PCh. 12 - Prob. 141PCh. 12 - Prob. 142PCh. 12 - Prob. 143PCh. 12 - Prob. 144PCh. 12 - Prob. 145PCh. 12 - Prob. 146PCh. 12 - Prob. 147PCh. 12 - Air is cooled as it flows through a 30-cm-diameter...Ch. 12 - Prob. 149PCh. 12 - Prob. 152PCh. 12 - Prob. 155PCh. 12 - Prob. 156PCh. 12 - Prob. 157PCh. 12 - Prob. 158PCh. 12 - Prob. 159PCh. 12 - Prob. 160PCh. 12 - Prob. 161PCh. 12 - Prob. 162PCh. 12 - Prob. 163PCh. 12 - Prob. 164PCh. 12 - Assuming you have a thermometer and a device to...
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- Air enters a nozzle at 0.5 MPa, 420 K, and . Approximating the flow as isentropic, determine the pressure and temperature of air at a location where the air velocity equals the speed of sound. What is the ratio of the area at this location to the entrance area? assuming the entrance velocity is negligible.arrow_forwardDetermine the speed of sound in air at (a) 300 K and (b) 1000 K. Determine the Mach number of an aircraft moving in air at a velocity of 240 m/s for both cases.arrow_forwardAir flowing at 32 kPa, 240 K, and Ma1 = 3.6 is forced to undergo an expansion turn of 15°. Determine the Mach number, pressure, and temperature of air after the expansion.arrow_forward
- I need the answer as soon as possiblearrow_forwardHelium enters a nozzle at 0.5 MPa, 600 K, and a negligible entrance velocity. Assuming isentropic flow, determine the pressure and temperature of helium at a location where the velocity equals the speed of sound. What is the ratio of the area at this location to the entrance area?arrow_forwardSolve the question, immediately.arrow_forward
- In a wind tunnel air enters with a velocity of 200kmph. The static pressure and temperature of the air at the inlet of the tunnel is 110kPa and 27°C respectively. Determine Mach number, stagnation temperature, stagnation pressure and the stagnation density on a test model installed in the wind tunnel. The size of the tunnel is given as 1m x1m square cross-section. Determine the mass flow rate of the air. For air assume R=287J/kgK ; γ=1.4.arrow_forwardHelium enters a nozzle at 0.5 MPa, 600 K, and a velocity of 120 m/s. Assuming isentropic flow, determine the pressure and temperature of helium at a location where the velocity equals the speed of sound. What is the ratio of the area at this location to the entrance area?arrow_forwardDoes the Mach number of a gas flowing at a constant velocity remain constant? Explain.arrow_forward
- What is the Mach Number of an air with a velocity of 250 m/s, at a temperature at 2800 meters?arrow_forwardA cylinder device is filled with 2.5 ?g of air at a pressure of 250 ?pa and initially at atemperature of 300?. It is compressed isobarically for ten seconds, and the specificwork rate is found to be −15 ?J / ?g / ? throughout the process. Calculate the final to-initial volume ratio, ?2⁄?1, and initial-to-final temperature ratio, ?1⁄?2.arrow_forwardCarbon dioxide flows steadily through a varying cross- sectional-area duct such as a nozzle at a mass flow rate of 3 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 a pressure of 200 kPa. The duct is designed so that the flow can be approximated as isentropic. Determine the following parameters at each location along the duct that corresponds to a pressure drop of 200 kPa: (i) density; (ii) velocity: (iii) flow area; (iv) mach number. You may assume: • Carbon dioxide is an ideal gas with constant specific heats at room temperature; • Flow through the duct is steady, one-dimensional and isentropic. Use c, 0 846 kJ/kgk andk = 1.289 throughout the calculations, which are the constant-pressure specific heat and specific heat ratio values of carbon dioxide at room temperature. The gas constant of carbon dioxide is R = 0.1889 kJ/kg K.arrow_forward
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