FLUID MECHANICS-PHYSICAL ACCESS CODE
8th Edition
ISBN: 9781264005086
Author: White
Publisher: MCG
expand_more
expand_more
format_list_bulleted
Textbook Question
Chapter 9, Problem 9.71P
A converging-diverging nozzle has a throat area of 10 cm2 and an exit area of 28.96 cm2. A normal shock stands in the exit when the back pressure is sea-level standard. If the upstream tank temperature is 400 K. estimate (a) the tank pressure and (b) the mass How.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solutionStudents have asked these similar questions
Air flows through a converging–diverging nozzle betweentwo large reservoirs, as shown in Fig. A mercurymanometer between the throat and the downstream reservoirreads h = 15 cm. Estimate the downstream reservoirpressure. Is there a normal shock in the flow? If so, does itstand in the exit plane or farther upstream?
Air, from a reservoir at 350 K and 500 kPa, fl ows througha converging–diverging nozzle. The throat area is 3 cm2. Anormal shock appears, for which the downstream Machnumber is 0.6405. (a) What is the area where the shockappears? Calculate (b) the pressure and (c) the temperaturedownstream of the shock.
Air flows isentropically through a variable-area duct. Atsection 1, A1= 20 cm2, p1= 300 kPa, ρ1= 1.75 kg/m3, andMa1= 0.25. At section 2, the area is exactly the same, butthe flow is much faster. Compute (a) V2, (b) Ma2, (c) T2,and (d ) the mass flow. (e) Is there a sonic throat betweensections 1 and 2? If so, find its area.
Chapter 9 Solutions
FLUID MECHANICS-PHYSICAL ACCESS CODE
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
- 1. Air, with stagnation conditions of 800 kPa and 100 °C, ex pands isentropically to a section of a duct where A₁ = 20 cm² and p₁ = 47 kPa. Compute ( a ) Ma₁ , ( b ) the throat area , and ( c ) m . At section 2 between the throat and section 1, the area is 9 cm². (d) Estimate the Mach number at sec tion 2. Plz sketch and solve itarrow_forwardConsider the venturi nozzle of Fig. , with D = 5 cmand d = 3 cm. Stagnation temperature is 300 K, and theupstream velocity V1 = 72 m/s. If the throat pressure is124 kPa, estimate, with isentropic flow theory, (a) p1,(b) Ma2, and (c) the mass flow.arrow_forwardAir, supplied by a reservoir at 450 kPa, flows through a con verging-diverging nozzle whose throat area is 12 cm². A nor mal shock stands where A1 = 20 cm². (a) Compute the pres sure just downstream of this shock. Still farther downstream, at A2 = 30 cm² estimate (b) p3, (c) A3, and (d) Ma3.arrow_forward
- Air flows isentropically in a channel. Properties at section1 are V1 = 250 m/s, T1 = 330 K, and p1 = 80 kPa. Atsection 2 downstream, the temperature has dropped to 0°C.Find (a) the pressure, (b) velocity, and (c) Mach number atsection 2.arrow_forwardAir flows isentropically in a converging-divergingnozzle with a throat area of 3 cm2. At section 1, the pressureis 101 kPa, the temperature is 300 K, and the velocityis 868 m/s. (a) Is the nozzle choked? Determine(b) A1 and (c) the mass flow. Suppose, without changingstagnation conditions or A1, the (flexible) throat isreduced to 2 cm2. Assuming shock-free flow, will therebe any change in the gas properties at section 1? If so,compute new p1, V1, and T1 and explain.arrow_forwardConsider the Gulfstream IV flying at Mach = 0.8 at an altitude with atmospheric pressure of 33,283.40-Pa. Calculate thrust required assuming a weight of 73,000-lb. Airplane data: S = 950 ft2, AR = 5.92, ?Do = 0.015, and K = 0.08. The thrust required. (in lbf)arrow_forward
- Figure shows the exit of a converging–diverging nozzle,where an oblique shock pattern is formed. In the exitplane, which has an area of 15 cm2, the air pressure is 16 kPaand the temperature is 250 K. Just outside the exit shock,which makes an angle of 50° with the exit plane, the temperatureis 430 K. Estimate (a) the mass flow, (b) the throatarea, (c) the turning angle of the exit flow, and, in the tanksupplying the air, (d ) the pressure and (e) the temperature.arrow_forwardConsider the Gulfstream IV flying at Mach = 0.8 at an altitude with atmospheric pressure of 33,283.40-Pa. Calculate thrust required assuming a weight of 73,000-lb. Airplane data: S = 950 ft2, AR = 5.92, CDo = 0.015, and K = 0.08. The thrust required. (in lbf)arrow_forwardAir flows from a tank through a nozzle into the standardatmosphere, as in Fig. A normal shock stands in theexit of the nozzle, as shown. Estimate (a) the pressure inthe tank and (b) the mass flow.arrow_forward
- 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_forwardWhen a pitot-static tube is placed in a supersonic flow, the probe reads P = 190 kPa and P = 150 kPa. If the stagnation temperature is 400 K, estimate the freestream Mach number and velocity.arrow_forwardConsider an oblique shock wave with a wave angle of 30◦ in a Mach 4flow. The upstream pressure and temperature are 2.65 × 104 N/m2 and223.3 K, respectively (corresponding to a standard altitude of 10,000 m).Calculate the pressure, temperature, Mach number, total pressure, and totaltemperature behind the wave and the entropy increase across the wave.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 PressMechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSONThermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
- Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEYMechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage LearningEngineering 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