Fluid Mechanics: Fundamentals and Applications
4th Edition
ISBN: 9781259696534
Author: Yunus A. Cengel Dr., John M. Cimbala
Publisher: McGraw-Hill Education
expand_more
expand_more
format_list_bulleted
Videos
Question
Chapter 12, Problem 98CP
To determine
(a)
The effect of decreasing Mach number on Stagnation Temperature
To determine
(b)
The effect of decreasing Mach number on Stagnation pressure
To determine
(c)
The effect of decreasing Mach number on entropy.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solution
Students have asked these similar questions
n aircraft is flying at an altitude of 12000 metres (T=216.65 K. p = 0.193 bar) at a Mach number of 0.82.
The cross sectional area of the inlet diffuser before the L.P. compressor stage is 0.5 m. Determine
(a) the mass of air entering the compressor per second (b) the speed of the aircraft (c) the stagnation
%3D
pressure and temperature of air at the diffuser entry.
3. Air enters a converging-diverging nozzle at 1.50 MPa and 900 K with a negligible velocity. The flow is
steady, one-dimensional, and isentropic with k =1.4. For an exit Mach number of Ma = 2.4 and a throat area
of 15 cm2, determine (a) the T, P and p in the throat, (b) the T, P and p in the exit plane, including the exit
area, and (c) the mass flow rate through the nozzle
Air enters a converging–diverging nozzle, as shown at 1.0 MPa and 800 K with negligible velocity. The flow is steady, one-dimensional, and isentropic with k = 1.4. For an exit Mach number of Ma = 2 and a throat area of 20 cm2, determine (a) the throat conditions, (b) the exit plane conditions, including the exit area, and (c) the mass flow rate through the nozzle.
Chapter 12 Solutions
Fluid Mechanics: Fundamentals and Applications
Ch. 12 - What is dynamic temperature?Ch. 12 - Calculate the stagnation temperature and pressure...Ch. 12 - Prob. 6PCh. 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. 72EPCh. 12 - Prob. 73P
Ch. 12 - Prob. 74PCh. 12 - Prob. 75PCh. 12 - For an ideal gas flowing through a normal shock,...Ch. 12 - Prob. 77CPCh. 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. 80CPCh. 12 - Prob. 81CPCh. 12 - Prob. 82CPCh. 12 - Argon gas enters a constant cross-sectional area...Ch. 12 - Prob. 84EPCh. 12 - Prob. 85PCh. 12 - Prob. 86PCh. 12 - Prob. 87EPCh. 12 - Prob. 88PCh. 12 - Prob. 89PCh. 12 - Prob. 90PCh. 12 - Prob. 91PCh. 12 - Prob. 93CPCh. 12 - Prob. 94CPCh. 12 - Prob. 95CPCh. 12 - Prob. 96CPCh. 12 - Prob. 97CPCh. 12 - Prob. 98CPCh. 12 - Prob. 99CPCh. 12 - Prob. 100CPCh. 12 - Prob. 101PCh. 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 12-cm-diameter adiabatic duct at...Ch. 12 - Prob. 105PCh. 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. 110PCh. 12 - Prob. 112PCh. 12 - Prob. 113PCh. 12 - Prob. 114PCh. 12 - Prob. 115PCh. 12 - Prob. 116EPCh. 12 - A subsonic airplane is flying at a 5000-m altitude...Ch. 12 - Prob. 118PCh. 12 - Prob. 119PCh. 12 - Prob. 120PCh. 12 - Prob. 121PCh. 12 - Prob. 122PCh. 12 - Prob. 123PCh. 12 - An aircraft flies with a Mach number Ma1=0.9 at an...Ch. 12 - Prob. 125PCh. 12 - Helium expands in a nozzle from 220 psia, 740 R,...Ch. 12 - Prob. 127PCh. 12 - Prob. 128PCh. 12 - Prob. 129PCh. 12 - Prob. 130PCh. 12 - Prob. 131PCh. 12 - Prob. 132PCh. 12 - Prob. 133PCh. 12 - Prob. 134PCh. 12 - Prob. 135PCh. 12 - Prob. 136PCh. 12 - Prob. 137PCh. 12 - Prob. 138PCh. 12 - Air is cooled as it flows through a 30-cm-diameter...Ch. 12 - Prob. 140PCh. 12 - Prob. 141PCh. 12 - Prob. 142PCh. 12 - Prob. 145PCh. 12 - Prob. 148PCh. 12 - Prob. 149PCh. 12 - Prob. 150PCh. 12 - Prob. 151PCh. 12 - Prob. 153PCh. 12 - Prob. 154PCh. 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 - Assuming you have a thermometer and a device to...
Knowledge Booster
Learn more about
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
- (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. -arrow_forwardConsider supersonic Fanno flow that is decelerated to sonic velocity (Ma = 1) at the duct exit as a result of frictional effects. If the duct length is increased further, will the flow at the duct exit be supersonic, subsonic, or remain sonic? Will the mass flow rate of the fluid increase, decrease, or remain constant as a result of increasing the duct length?arrow_forwardConsider subsonic Fanno flow accelerated to sonic velocity (Ma = 1) at the duct exit as a result of frictional effects. If the duct length is increased further, will the flow at the duct exit be supersonic, subsonic, or remain sonic? Will the mass flow rate of the fluid increase, decrease, or remain constant as a result of increasing the duct length?arrow_forward
- How does the Mach number affect the behavior of compressible flow in a supersonic nozzle?arrow_forwardMach number at a certain section in a diverging part of a c-d nozzle is 0.7. At farther section (towards the exit), Mach number reduces to 0.4. Hence, the cross-sectional area of the farther section is greater byarrow_forwardAir flows isentropically through a duct. At section 1, thepressure and temperature are 250 kPa and 125°C, andthe velocity is 200 m/s. At section 2, the area is 0.25 m2 andthe Mach number is 2.0. Determine (a) Ma1; (b) T2; (c) V2;and (d ) the mass fl ow.arrow_forward
- Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.6. The pressure and temperature of air are 52 kPa and 270 K, respectively. Now, helium undergoes a normal shock under the same conditions. Calculate the entropy changes of air and helium across the normal shock. The properties of air are R = 0.287 kJ/kg-K and cp= 1.005 kJ/kg-K, and the properties of helium are R=2.0769 kJ/kg-K and cp=5.1926 kJ/kg.K. The entropy change for air is The entropy change for helium is kJ/kg-K. kJ/kg-K.arrow_forwardConsider air entering a heated duct at p1 = 1 atm and T1 = 288 K. Ignore the effect of friction. Calculate the amount of heat per unit mass (in joules per kilogram) necessary to choke the flow at the exit of the duct for an inlet Mach number of M1 = 2.2.arrow_forward5- An aircraft is flying at an altitude of (12000 m) (T = 216.65 k, P = 0.193bar) at a Mach number of (0.82). The cross-sectional area of the inlet diffuser is (0.5 m2).Determine: (a) The mass of air entering the compressor per second. (b) The speed of aircraft. (c) The stagnation pressure and temperature of air at the diffuser entry.arrow_forward
- Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.6. If the pressure and temperature of air are 58 kPa and 270 K, respectively, upstream of the shock, calculate the pressure, temperature velocity, Mach number, and stagnation pressure downstream of the shock. Calculate the entropy changes of air and helium across the normal shock wavearrow_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_forward(a) Write Area-Velocity relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (b) Write Area-density relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (c) Write Area-Mach relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (d) Plot the variation of density, pressure, temperature, velocity and Mach number for compressible flows through a supersonic Convergent-Divergent nozzle Note: Do NOT derive above relations.arrow_forward
arrow_back_ios
SEE MORE QUESTIONS
arrow_forward_ios
Recommended textbooks for you
Elements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University Press
Mechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSON
Thermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEY
Mechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage Learning
Engineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEY
Elements Of Electromagnetics
Mechanical Engineering
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Oxford University Press
Mechanics of Materials (10th Edition)
Mechanical Engineering
ISBN:9780134319650
Author:Russell C. Hibbeler
Publisher:PEARSON
Thermodynamics: An Engineering Approach
Mechanical Engineering
ISBN:9781259822674
Author:Yunus A. Cengel Dr., Michael A. Boles
Publisher:McGraw-Hill Education
Control Systems Engineering
Mechanical Engineering
ISBN:9781118170519
Author:Norman S. Nise
Publisher:WILEY
Mechanics of Materials (MindTap Course List)
Mechanical Engineering
ISBN:9781337093347
Author:Barry J. Goodno, James M. Gere
Publisher:Cengage Learning
Engineering Mechanics: Statics
Mechanical Engineering
ISBN:9781118807330
Author:James L. Meriam, L. G. Kraige, J. N. Bolton
Publisher:WILEY
Intro to Compressible Flows — Lesson 1; Author: Ansys Learning;https://www.youtube.com/watch?v=OgR6j8TzA5Y;License: Standard Youtube License