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 7P
To determine
Static pressure and temperature of the air in this state.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solution
Students have asked these similar questions
4-Steam flows through a device with a stagnation pressure of 120 psia, a
stagnation temperature of 7008F, and a velocity of 900 ft/s. Assuming ideal-
gas behavior, determine the static pressure and temperature of the steam at
this state.
Argon is accelerated in a nozzle from 32 m/s at 666 K to 441 m/s and 196 kPa. If the heat loss is equal to 5.1 kJ/kg, determine the gas temperature at outlet in K to 1 decimal place. Take the gas constant as 0.2 (kPa m3)/(kg K) and assume constant specific heats cp=0.5 kJ/(kg K) and cv=0.3 kJ/(kg K).
4.
Carbon 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 cp=…
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
- 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?arrow_forward1- An ideal gas with k = 1.4 is flowing through a nozzle such that the Mach number is 2.4 where the flow area is 25 cm2. Assuming the flow to be isentropic, determine the flow area at the location where the Mach number is 1.2arrow_forward(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_forward
- For the specific volume of wet steam, SV=(1-Xv)SV (liq) + XvSV (vapor). Entropy is also calculated this way. If a tank initially has 5kg of wet steam with mass of vapor =1 kg at 100 kPa, and it is heated such that saturated vapor remains in the tank. Assuming that the process is in constant volume, what will be the entropy change of the steam (Kj/K)?arrow_forwardFor an ideal gas flowing through a normal shock, develop a relation for V2/V1 in terms of k, Ma1, and Ma2.arrow_forward1- Air enters a nozzle at 0.2 MPa, 350 K, and a stagnation velocity. Assuming isentropic flow, 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?arrow_forward
- In an ideal nozzle, the enthalpy change of the gas is 69.4 kJ/kg. Assuming the initial velocity is negligible what is the final velocity (Enter your answer to the nearest whole number of m/s)?arrow_forwardThe fluid is heated from 125 degrees Fahrenheit to 225 degrees Fahrenheit. Consider an ideal gas with the following characteristics: R = 85 ft-lbf/lbm-R Cp = 0.35 + 0.000325T BTU/lbm-R If the heating is at constant volume, compute for (a) the change in internal energy, (b) the change in enthalpy, and (c) the change in entropy. If the heating is at constant pressure, compute for (d) the change in entropy, and (e) the value of k at 160 degrees Celsius. If the fluid undergoes an isentropic process, determine (f) non-flow work and (g) steady-flow work. (For item f and g, use the value of k at 160 degrees Celsius). Note: The unit should be in metric system. Should have given, required and the solution.arrow_forwardAir enters a compressor at a stagnation state of 100 kPa and 27 ∘C. If it has to be compressed toa stagnation pressure of 900 kPa, calculate the power input to the compressor when the massflow rate is 0.02 kg s−1. Assume the compression process to be isentropic.arrow_forward
- Compressed air from the compressor of a gas turbine enters the combustion chamber at T1 = 700 K, P1 = 560 kPa, and Ma1 = 0.2 at a rate of 0.3 kg/s. Via combustion, heat is transferred to the air at a rate of 300 kJ/s as it flows through the duct with negligible friction. Determine the Mach number at the duct exit and the drop in stagnation pressure P01 – P02 during this process. Take the properties of air to be k = 1.4, cp = 1.005 kJ/kg·K, and R = 0.287 kJ/kg·K. The Mach number at the duct exit is____ . The drop in stagnation pressure is____ kPa.arrow_forwardAir flows steadily through a varying cross-sectional area duct such as a nozzle at a mass flow rate of 10 lb/s. The air enters the duct at a pressure of 200 lb/in2 and 445°F with a low velocity, and it expands in the nozzle to an exit pressure of 30 lb/in2. The duct is designed so that the flow can be approximated as isentropic. Determine the density, velocity, flow area, and Mach number at each location along the duct that corresponds to an overall pressure drop of 30 lb/in2.arrow_forwardThe compressor of a jet engine tested at sea level on a stationary test bed on a day when the atmospheric temperature and pressure is 298 K and 101kPa, respectively. When running at its design operating point, the masss flow rate through the compressor is measured as 15 kg/s and the rational speed is 6200 rpm. Determine the mass flow rate and the rational speed when the compressor is operating at the design operating point during high altitude cruise with an onlet stagnation temperature of 236 K and an inlet stagnation pressure of 10.2 kpa. The design pressure ratio of compressor is 20. If the compressor isentropic efficiency is determined from the test to be 85=, calculate the power input at the cruise condition. Assume for air that y=1. 4 and Cp=1005 kJ/kg-K throughout.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
Thermodynamic Availability, What is?; Author: MechanicaLEi;https://www.youtube.com/watch?v=-04oxjgS99w;License: Standard Youtube License