Fluid Mechanics
8th Edition
ISBN: 9780073398273
Author: Frank M. White
Publisher: McGraw-Hill Education
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
A converging-diverging nozzle has a throat area of 10 cm2and an exit area of 28.96 cm2. A normal shock stands in theexit when the back pressure is sea-level standard. If theupstream tank temperature is 400 K, estimate (a) the tankpressure and (b) the mass fl ow.
Air at P1 = 1 MPa, T1 = 600 °C and V1 = 150 m/s enters a converging nozzle. The exit area is A2 = 50 cm2 and the back pressure is P2 = 0.7 MPa. What is the mass flow rate (kg/s) through the nozzle? What the is Mach number at the nozzle exit? What would be the flow rate you calculate if you assumed isothermal flow?
Air 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.
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
- e. Q3 / Air, from a reservoir at 350 K and 500 kPa, flows through a converging diverging nozzle. The throat area is 3 cm². A normal shock appears, for which the downstream Mach number is 0.6405. (a) What is the area where the shock appears? Calculate (b) the pressure and (c) the temperature downstream of the shock.arrow_forwardAn air formed a shockwave with a Mach of 2.3. What is the pressure downstream when the pressure before the normal shock is at a condition of 2500 m?arrow_forwardA convergent divergent diffuser is exposed to air at pressure of 80kPa and temperature of 350K and Mach number Mi=2.5 as shown in fig. The inlet area Ai = 20 cm2, throat area = 10 cm2, and exit area = 25 cm2. 1- If the back pressure is 650kPa the shock wave is take place at the divergent part find: Throat Mach number , mass flow rate, Shock wave location ,exit Mach number. 2- If the incoming Mach number is decrease to 1.8 State the flow condition through the duct and find, the mass flow rate , exit pressure and Mach number M=2.5, P=80, T=350 Flow condition through the duct for CASE 1)arrow_forward
- Q6: Air following through constant area duct encounters stationary shock as shown in figure. Find the Mach number, temperature, pressure, stagnation pressure, stagnation temperature and velocity after the shock. Ans.: M2 = 0.6746, T2 = 344 K, p2 = 137 kPa, To = 375 K, po = 186 kPa. V1=500 m/s P;=50 kPa 1-250 K → (1) | (2)arrow_forwardAir 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?arrow_forwardQ2: Air flows isentropically through converging nozzle which has a throat of 7 cm?. The stagnation conditions are 130 kpa and 380 K. Find the exit pressure and mass flow rate if the atmospheric pressure is: (a) 88 kpa. (b) 40 kpa. (Take: K = 1.4, C, =1005 J/kg.k and R = 287 J/kg.k for air)arrow_forward
- Consider 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_forwardQ2: Air flows isentropically through converging nozzle which has a throat of 7 cm?. The stagnation conditions are 130 kpa and 380 K. Find the exit pressure and mass flow rate if the atmospheric pressure is: (a) 88 kpa. (b) 40 kpa. (Take: K = 1.4, Cp =1005 J/kg.k and R = 287 J/kg.k for air) %3!arrow_forwardA turbine nozzle vane at high speed exhibits a normal shock. The flow is modelled as analogous to that through a convergent-divergent de Laval nozzle with a normal shock at the nozzle exit. Just upstream of the shock, the exit Mach number Me = 1.09, the absolute static pressure pe = 280 kPa, the static temperature Te = 586 K, the ratio of specific heats of the combustion productsk = 1.35, and the constant pressure specific heat capacity Cp = 1027 J-kg "K-1. Assuming the combustion products are constant property ideal gasses, determine the density of the combustion products pp after the shock. State your answer in kg m to two decimal places and enter the numerical value only.arrow_forward
- Air, with stagnation conditions of 800 kPa and 100°C, ex pands isentropically to a section of a duct where A_{1} = 20 cm² and p_{1} = 47kPa . 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 section 2.arrow_forwardsection If the back pressure is low enough and the throat is sonic, the Mach number is more than I in a/an during flow in a convergent-divergent nozzle. 1. diverging X2. converging X 3. entry X 4. throatarrow_forwardFor given air flow with Mach number in test section (i.e. at CD nozzle exit), Me = 8, T01 = 300 K, pressure in test section = 4000 Pa. (1) What is the value of static temperature, stagnation temperature and stagnation pressure in the test section? (2) What is the value of stagnation pressure in the storage thank? (3) What do you conclude about state of air? (4) What is the solution to rectify this problem. i.e. (5)What is the minimum temperature of air should you take in reservoir tank? At this condition, what is mass flow rate in test section? Low pressure air chamber High pressure air storage Storage tank T01 = 300K P01 = ? Settling chamber Pressure regulator Nozzle Screens Test-section Pe = 4000 Pa Me = 8 Te = ? K Sonic throat P0e =? T0e = ? Blow down wind Tunnel (Open circuit type) Diffuser Second throat vacuum tankarrow_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