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 158P
To determine
The mach number of the flow.
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How does the parameter Ma* differ from the Mach number Ma?
Air is flowing in a wind tunnel at 12°C and 66 kPa at a velocity of 190 m/s. The Mach number of the flow is (a) 0.56 m/s (b) 0.65 m/s (c) 0.73 m/s (d ) 0.87 m/s (e) 1.7 m/s
(b) Air flows through a cylindrical duct at a rate of 2.3 kg/s. Friction between air and the
duct and friction within air can be neglected. The diameter of the duct is 10cm and the
air temperature and pressure at the inlet are T₁ 450 K and P₁ = 200 kPa. If the Mach
number at the exit is Ma2
determine the rate of heat transfer and the pressure
difference across the duct. The constant pressure specific heat of air is cp = 1.005
kJ/kg-K. The gas constant of air is R = 0.287 kJ/kg-K and assume k = 1.4.
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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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Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.Similar questions
- How is the Mach number of a flow defined? What does a Mach number of 2 indicate?arrow_forwardThe speed of a spacecraft is given to be 1250 km/h in atmospheric air at −40°C. The Mach number of this flow is (a) 35 .9 (b) 0.85 (c) 1.0 (d ) 1.13 (e) 2.74arrow_forwardI need help on 3bii and ivarrow_forward
- An aircraft is reported to be cruising in still air at −20°C and 40 kPa at a Mach number of 0.86. The velocity of the aircraft is (a) 91 m/s (b) 220 m/s (c) 186 m/s (d ) 274 m/s (e) 378 m/sarrow_forwardI need the answer as soon as possiblearrow_forwardaircraft flies at the same Mach number but 50 m/s slower at 8 km compared to its speed at sea level. Find this Mach number a. 1.45 b. 1.55 c. 2.25 d. 1.65 e. 2.50.arrow_forward
- I need the answer as soon as possiblearrow_forward1- For flow of a compressible fluid from a storage tank through a converging-diverging channel operating under Choked conditions O(a) The pressure at the exit will be equal to the sonic pressure O (b) The flow in the diverging section must be supersonic (c) The mass flow rate through the channel cannot be increased by changing the storage tank conditions (d) none of the abovearrow_forwardQuestion Four Air flows steadily adiabatically through a pipe with a cross-sectional of 0.002 m?. At the inlet of the duct, the pressure and temperature are 100 kPa and 50°C, respectively. At the exit of the duct, the temperature and velocity are 100°C and 600 m/s, respectively. Determine the Mach number and the velocity at the inlet section. Also, calculate the mass flow rate. Ans. M 1.884, vi = 678.7 m/s, m = 1.46 kg/s.arrow_forward
- Air at 27 °C and 100 kPa enters in a steady flow to a nozzle at a velocity of 100 m/s. If the inlet area of the nozzle is 0.5 m², what is the mass flow rate through the system?arrow_forwardAir at 26 psia, 320°F, and Mach number Ma = 0.7 flows through a duct. Calculate the velocity and the stagnation pressure, temperat and density of air. The properties of air are R = 0.06855 Btu/lbm-R = 0.3704 psia-ft3/lbm-R and k=1.4. The velocity of air is ft/s. The stagnation temperature of air is The stagnation pressure of air is The stagnation density of air is R. psia. | lbm/ft³.arrow_forwardWhat is the Mach Number of an air with a velocity of 250 m/s, at a temperature at 2800 meters?arrow_forward
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