Fluid Mechanics
8th Edition
ISBN: 9780073398273
Author: Frank M. White
Publisher: McGraw-Hill Education
expand_more
expand_more
format_list_bulleted
Videos
Textbook Question
Chapter 9, Problem 9.85P
A typical carbon dioxide tank for a paintball gun holds about 12 oz of liquid CO2. The tank is filled no more than one-third with liquid, which, at room temperature, maintains the gaseous phase at about 850 psia. (a) If a valve is opened that simulates a converging nozzle with an exit diameter of 0.050 in, what mass flow and exit velocity results? (b) Repeat the calculations for helium.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solution
Students have asked these similar questions
Q2 (a) In designing a nozzle why nozzle angle is not zero. Explain with the help of sketch.
Q2 (b) In designing a nozzle, what is the significance of stagnation properties?
Q2 (c) During Steam turbine construction, what is the purpose of shroud ring?
The converging–diverging nozzle shown in Fig. P3.22expands and accelerates dry air to supersonic speeds at theexit, where p 2 = 8 kPa and T 2 = 240 K. At the throat, p 1=284 kPa, T 1 = 665 K, and V 1 = 517 m/s. For steadycompressible fl ow of an ideal gas, estimate ( a ) the mass fl owin kg/h, ( b ) the velocity V 2 , and ( c ) the Mach number Ma 2 .
Consider a typical air flow around a cruising jetliner at 10km altitude. The speed is now 810 km/h, while the ambient conditions are 0.414 kg/m³ , 0.261 atm and -50°C. At the stagnation point, the temperature rises over by 25°C, while the density and pressure changes by more than 30% and 45 % respectively. Classify the following situations as compressible/incompressible flow
Chapter 9 Solutions
Fluid Mechanics
Ch. 9 - Prob. 9.1PCh. 9 - Prob. 9.2PCh. 9 - If 8 kg of oxygen in a closed tank at 200°C and...Ch. 9 - P9.4 Consider steady adiabatic airflow in a duct....Ch. 9 - Prob. 9.5PCh. 9 - Prob. 9.6PCh. 9 - Prob. 9.7PCh. 9 - Prob. 9.8PCh. 9 - P9.9 Liquid hydrogen and oxygen are burned in a...Ch. 9 - P9.10 A certain aircraft flics at 609 mi/h at...
Ch. 9 - Prob. 9.11PCh. 9 - Prob. 9.12PCh. 9 - Consider steam at 500 K and 200 kPa. Estimate its...Ch. 9 - Prob. 9.14PCh. 9 - Prob. 9.15PCh. 9 - Prob. 9.16PCh. 9 - Prob. 9.17PCh. 9 - Prob. 9.18PCh. 9 - Prob. 9.19PCh. 9 - Prob. 9.20PCh. 9 - P9.21 N?O expands isentropically through a duct...Ch. 9 - Given the pitot stagnation temperature and...Ch. 9 - Prob. 9.23PCh. 9 - Prob. 9.24PCh. 9 - Prob. 9.25PCh. 9 - Prob. 9.26PCh. 9 - P9.27 A pitot tube, mounted on an airplane flying...Ch. 9 - Prob. 9.28PCh. 9 - Prob. 9.29PCh. 9 - Prob. 9.30PCh. 9 - Prob. 9.31PCh. 9 - Prob. 9.32PCh. 9 - Prob. 9.33PCh. 9 - Prob. 9.34PCh. 9 - Prob. 9.35PCh. 9 - P9.36 An air tank of volume 1.5 m3 is initially at...Ch. 9 - Make an exact control volume analysis of the...Ch. 9 - Prob. 9.38PCh. 9 - Prob. 9.39PCh. 9 - Prob. 9.40PCh. 9 - Prob. 9.41PCh. 9 - Prob. 9.42PCh. 9 - Prob. 9.43PCh. 9 - Prob. 9.44PCh. 9 - It is desired to have an isentropic airflow...Ch. 9 - Prob. 9.46PCh. 9 - Prob. 9.47PCh. 9 - Prob. 9.48PCh. 9 - Prob. 9.49PCh. 9 - Prob. 9.50PCh. 9 - Prob. 9.51PCh. 9 - Prob. 9.52PCh. 9 - Prob. 9.53PCh. 9 - Prob. 9.54PCh. 9 - Prob. 9.55PCh. 9 - Prob. 9.56PCh. 9 - Prob. 9.57PCh. 9 - Prob. 9.58PCh. 9 - Prob. 9.59PCh. 9 - Prob. 9.60PCh. 9 - Prob. 9.61PCh. 9 - Prob. 9.62PCh. 9 - Prob. 9.63PCh. 9 - Prob. 9.64PCh. 9 - Prob. 9.65PCh. 9 - Prob. 9.66PCh. 9 - Prob. 9.67PCh. 9 - Prob. 9.68PCh. 9 - Prob. 9.69PCh. 9 - Prob. 9.70PCh. 9 - A converging-diverging nozzle has a throat area of...Ch. 9 - Prob. 9.72PCh. 9 - Prob. 9.73PCh. 9 - Prob. 9.74PCh. 9 - Prob. 9.75PCh. 9 - Prob. 9.76PCh. 9 - P9.77 A perfect gas (not air) expands...Ch. 9 - Prob. 9.78PCh. 9 - P9.79 A large tank, at 400 kPa and 450 K, supplies...Ch. 9 - Prob. 9.80PCh. 9 - Prob. 9.81PCh. 9 - Prob. 9.82PCh. 9 - 1*9.83 When operating at design conditions (smooth...Ch. 9 - Prob. 9.84PCh. 9 - A typical carbon dioxide tank for a paintball gun...Ch. 9 - Prob. 9.86PCh. 9 - Prob. 9.87PCh. 9 - Prob. 9.88PCh. 9 - Prob. 9.89PCh. 9 - Prob. 9.90PCh. 9 - Prob. 9.91PCh. 9 - Prob. 9.92PCh. 9 - Prob. 9.93PCh. 9 - Prob. 9.94PCh. 9 - Prob. 9.95PCh. 9 - Prob. 9.96PCh. 9 - Prob. 9.97PCh. 9 - Prob. 9.98PCh. 9 - Prob. 9.99PCh. 9 - Prob. 9.100PCh. 9 - Prob. 9.101PCh. 9 - Prob. 9.102PCh. 9 - Prob. 9.103PCh. 9 - Prob. 9.104PCh. 9 - Prob. 9.105PCh. 9 - Prob. 9.106PCh. 9 - Prob. 9.107PCh. 9 - Prob. 9.108PCh. 9 - P9.109 A jet engine at 7000-m altitude takes in 45...Ch. 9 - Prob. 9.110PCh. 9 - Prob. 9.111PCh. 9 - Prob. 9.112PCh. 9 - Prob. 9.113PCh. 9 - Prob. 9.114PCh. 9 - Prob. 9.115PCh. 9 - Prob. 9.116PCh. 9 - P9.117 A tiny scratch in the side of a supersonic...Ch. 9 - Prob. 9.118PCh. 9 - Prob. 9.119PCh. 9 - Prob. 9.120PCh. 9 - Prob. 9.121PCh. 9 - Prob. 9.122PCh. 9 - Prob. 9.123PCh. 9 - Prob. 9.124PCh. 9 - Prob. 9.125PCh. 9 - Prob. 9.126PCh. 9 - Prob. 9.127PCh. 9 - Prob. 9.128PCh. 9 - Prob. 9.129PCh. 9 - Prob. 9.130PCh. 9 - Prob. 9.131PCh. 9 - Prob. 9.132PCh. 9 - Prob. 9.133PCh. 9 - P9.134 When an oblique shock strikes a solid wall,...Ch. 9 - Prob. 9.135PCh. 9 - Prob. 9.136PCh. 9 - Prob. 9.137PCh. 9 - Prob. 9.138PCh. 9 - Prob. 9.139PCh. 9 - Prob. 9.140PCh. 9 - Prob. 9.141PCh. 9 - Prob. 9.142PCh. 9 - Prob. 9.143PCh. 9 - Prob. 9.144PCh. 9 - Prob. 9.145PCh. 9 - Prob. 9.146PCh. 9 - Prob. 9.147PCh. 9 - Prob. 9.148PCh. 9 - Prob. 9.149PCh. 9 - Prob. 9.150PCh. 9 - Prob. 9.151PCh. 9 - Prob. 9.152PCh. 9 - Prob. 9.153PCh. 9 - Prob. 9.154PCh. 9 - Prob. 9.155PCh. 9 - Prob. 9.156PCh. 9 - The Ackeret airfoil theory of Eq. (9.104) is meant...Ch. 9 - Prob. 9.1WPCh. 9 - Prob. 9.2WPCh. 9 - Prob. 9.3WPCh. 9 - Prob. 9.4WPCh. 9 - Prob. 9.5WPCh. 9 - Prob. 9.6WPCh. 9 - Prob. 9.7WPCh. 9 - Prob. 9.8WPCh. 9 - FE9.1 For steady isentropic flow, if the absolute...Ch. 9 - FE9.2 For steady isentropic flow, if the density...Ch. 9 - Prob. 9.3FEEPCh. 9 - Prob. 9.4FEEPCh. 9 - Prob. 9.5FEEPCh. 9 - Prob. 9.6FEEPCh. 9 - Prob. 9.7FEEPCh. 9 - Prob. 9.8FEEPCh. 9 - Prob. 9.9FEEPCh. 9 - Prob. 9.10FEEPCh. 9 - Prob. 9.1CPCh. 9 - Prob. 9.2CPCh. 9 - Prob. 9.3CPCh. 9 - Prob. 9.4CPCh. 9 - Prob. 9.5CPCh. 9 - Prob. 9.6CPCh. 9 - Professor Gordon Holloway and his student, Jason...Ch. 9 - Prob. 9.8CPCh. 9 - Prob. 9.1DPCh. 9 - Prob. 9.2DP
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
- In Fig. water exits from a nozzle into atmosphericpressure of 101 kPa. If the fl ow rate is 160 gal/min and frictionis neglected, what is the gage pressure at section 1?( a ) 1.4 kPa, ( b ) 32 kPa, ( c ) 43 kPa, ( d ) 29 kPa, ( e ) 123 kPaarrow_forwardAir flows through a duct as in Fig, where A1 =24 cm2, A2 = 18 cm2, and A3 = 32 cm2. A normalshock stands at section 2. Compute (a) the mass flow,(b) the Mach number, and (c) the stagnation pressure atsection 3.arrow_forwardA gas, assumed ideal, flows isentropically from point 1,where the velocity is negligible, the pressure is 200 kPa,and the temperature is 300°C, to point 2, where the pressureis 40 kPa. What is the Mach number Ma2 if the gas is(a) air, (b) argon, or (c) CH4? (d ) Can you tell, withoutcalculating, which gas will be the coldest at point 2?arrow_forward
- In Fig. P3.127 the open jet of water at 20 ° C exits a nozzleinto sea-level air and strikes a stagnation tube as shown. If the pressure at the centerline at section 1 is 110 kPa, andlosses are neglected, estimate ( a ) the mass flow in kg/s and( b ) the height H of the fluid in the stagnation tube.arrow_forwardAir flows isentropically through a channel. From two points inside this channel 1st speed 240 m / s, temperature 320 K and pressure 170 kPa. At the 2nd point, the speed is 290 m / s and the pressure is 135 kPa. a-) Stop temperature at first point, stop pressure, stop density, Mach number, maximum speed and critical point speed b-) find the stopping pressure of the second point.arrow_forwardDuring the fall of 2005, Hurricane Wilma passed through the Gulf of Mexico. When the storm was classified as a category 5 hurricane, the pressure at the center of the hurricane was measured at 902 mbars. The highest wind velocity was 175 mph. Assuming the pressure far from the center of the hurricane was 1 bar and the air density was 1.2 kg m3 , estimate the pressure at the center of the hurricane. Comment on the difference in your prediction and the measured value and provide some rationale for the discrepancy. The answer should be p = 914 mbararrow_forward
- What is the Mach number of an airflow with a velocity of 2000m/s, at 2,000 ft altitude?arrow_forwardAir, at po = 160 lbf/in2 and To = 300 °F, fl ows isentropicallythrough a converging–diverging nozzle. At section 1,where A1 = 288 in2, the velocity is V1 = 2068 ft/s. Calculate(a) Ma1, (b) A*, (c) p1, and (d ) the mass flow, in slug/s.arrow_forwardIf losses are neglected in Fig. P3.133, for what water levelh will the flow begin to form vapor cavities at the throat ofthe nozzle?arrow_forward
- A hole is placed in the front of a cylinder to measure thestream velocity of sea-level fresh water. The measuredpressure at the hole is 2840 lbf/ft2. If the hole is misalignedby 12° from the stream and misinterpreted as stagnationpressure, what is the error in velocity?arrow_forwardCarbon dioxide convergent-divergent to a Lule of 60 m / s, 310 °C and 300 kPa in its case, it enters and leaves the Lule at a supersonic speed. Lule of carbon dioxide find the pressure, temperature and speed in his throat?arrow_forwardWhen the Apollo command module returned to earth from the moon, itentered the earth’s atmosphere at a Mach number of 36. Using the resultsfrom the present chapter for a calorically perfect gas with the ratio ofspecific heats equal to 1.4, predict the gas temperature at the stagnationpoint of the Apollo at Mach 36 at an altitude where the freestreamtemperature is 300 K. Comment on the validity of your answer.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