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 161P
To determine
The correct statement.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solution
Students have asked these similar questions
QUESTION 14
The fan of a turbofan engine is tested at high speed. The flow approaches the fan tip at a relative Mach number
M1rel = 1.19. An oblique shock forms at the fan tip leading edge, with a shock angle B = 87 degrees. Use cold-air-
standard assumptions and the two-dimensional oblique shock formulae to determine the relative Mach number M2rel
after the shock. State your answer to two decimal places. Partial credit is awarded for a reasonable approximation to
the correct numerical answer.
%3D
Part A
Outside air at a temperature of 25°C is drawn into the
duct and then heated along the duct at 210 kJ/kg. At
section 1 the temperature is T = 15°C and the
absolute pressure is 98 kPa. Neglect friction.
(Figure 1)
Determine the Mach number at section 2.
Express your answer using three significant figures.
vec
?
M2 =
Submit
Previous Answers Request Answer
X Incorrect; Try Again; 4 attempts remaining
Part B Complete previous part(s)
Part C Complete previous part(s)
Figure
Provide Feedback
50 mm
-2 m-
Question Two
Consider one-dimensional air isentropic flow through a duct. At a certain section of this duct,
the velocity is 360 m/s, the temperature is 45 °C, and the pressure is 120 kPa. Find the Mach
number and the stagnation temperature and pressure at this point in the flow. If the
temperature at some other point in the flow is 90 °C, find the Mach number and pressure at
this point in the flow.
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
- QUESTION 3 Dry air at 270C flows with a velocity of 360 kmph in an adiabatic wind tunnel. The static pressure is measured as 110kPa. Determine the Mach number, Stagnation temperature stagnation pressure and the stagnation density of air at the stagnation point on the nose tip of an aircraft model installed in the tunnel. Assume the cross-section area of the tunnel is 1.0 sq.m, Determine the mass flow rate of the air. For air take R = 287 J/kg; γ = 1.4;arrow_forwardAir flows at 200 m/s through the pipe. The temperature is 500 K and the absolute stagnation pressure is 200 kPa. Assume isentropic flow. For air R = 286.9 J/kg · K] and k = 1.40. (Figure 1) 0.3 m Determine the Mach number of the flow. Express your answer using three significant figures. M = Determine the mass flow. Express your answer using three significant figures. m = kg/sarrow_forwardAir flows through a converging-diverging (c-d) nozzle. It is supplied from a large air reservoir in which the temperature is 446 K and the pressure is 190 kPa. The velocity and the cross-sectional area at the nozzle exit are 594 m/s and 0.0005 m^2, respectively. Find the followings: Mach number at exit is Area of the throat is The mass flow rate of air is The exit temperature is The exit pressure isarrow_forward
- Which of the following statement is FALSE? (A) In adiabatic compressible flow in a conduit of constant crosssection, the Mach number can exceed 1.0 During fluid flow through many devices such as nozzles, diffusers, and turbine blade passages, flow quantities vary primarily in the flow direction only In a converging nozzle, the velocity of the gas stream will never exceed the sonic velocity, though in a converging- diverging nozzle supersonic velocities may be obtained in the diverging section (D) Mach number depends on the speed ofsound, which depends on the state of the fluid. E For an ideal gas, temperature decreases with increase in velocity.arrow_forwardFluid moves through a nozzle with Mach number of 1.5. Determine the following: (i) Speed of the fluid if the speed of sound in air is 325 m/s; (ii) Mach number if the speed of the fluid is 125 m/s.arrow_forwardQuestion B3 Consider an ideal nozzle of a rocket flying at an altitude where the ambient pressure and temperature are 26.5 kPa and 223 K, respectively. The nozzle is designed to expand air from its combustion chamber in which the pressure and temperature are Po kPa and 1400 K respectively to a Mach number of 2.00. The exit area of this nozzle is to be 0.196 m². You may assume the chamber temperature remains constant. 1- Calculate the nozzle supply pressure and throat area, mass flow rate through the nozzle and its thrust when operating at its design condition; DEN5242 (May 2019) Question B3 continued 2- Calculate the mass flow rate through the nozzle for a pressure ratio Po Ph of = 1.005. 3- Calculate the mass flow rate through the nozzle at a chamber pressure of 50 kPa; 4- Determine the chamber pressure at which a normal shock wave stands at the exit plane of the nozzle.arrow_forward
- Air is flowing in the converging-diverging nozzle shown in the figure below. A = 15 cm² A₁ = 10 cm² Determine the three critical pressure ratios. "pc1= i "pc2= i *pc3 = Shock i A = 25 cm² Determine the Mach number immediately upstream from the shock. Ma₁ = i Determine the Mach number immediately downstream from the shock. Ma₂ iarrow_forwardAir is flowing in a convergent nozzle. At a particular location within the nozzle the pressure is 280 kPa, the stream temperature is 345 K. and the velocity is 150 m/s. If the cross-sectional area at this location is 9.29 x 103 m², find: (a) The Mach number at this location, (b) The stagnation temperature and pressure. (c) The area, pressure, and temperature at the exit where M-1.0. (d) The mass rate of flow for the nozzle. Indicate any assumptions you may make and the source of data used in the solution.arrow_forwardIn a wind tunnel air enters with a velocity of 200kmph. The static pressure and temperature of the air at the inlet of the tunnel is 110kPa and 27°C respectively. Determine Mach number, stagnation temperature, stagnation pressure and the stagnation density on a test model installed in the wind tunnel. The size of the tunnel is given as 1m x1m square cross-section. Determine the mass flow rate of the air. For air assume R=287J/kgK ; γ=1.4.arrow_forward
- 5. An experimental centrifugal compressor is fitted with free-vortex guide vanes in order to reduce the relative air speed at inlet to the impeller. At the outer radius of the eye. air leaving the guide-vanes has a velocity of 91.5 m/s at 20 deg to the axial direction. Determine the inlet relative Mach number, assuming frictionless flow through the guide vanes, and the impeller total-to-total efficiency. Other details of the compressor and its operating conditions are: Impeller entry tip diameter. 0.457 m Impeller exit tip diameter. 0.762 m Slip factor 0.9 Radial component of velocity at impeller exit. 53.4m/s Rotational speed of impeller. 11 000 rev/min Static pressure at impeller exit. 223 kPa (abs.)arrow_forwardAir enters a duct with a Mach number of 2.0, and the temperature and pressure are 170 K and 0.7 bar, respectively. Heat transfer takes place while the flow proceeds down the duct. A converging section (A2/A3 = 1.45) is attached to the outlet as shown in Fig. Q4, and the exit Mach number is 1.0. Assume that the inlet conditions and exit Mach number remain fixed. Find the amount and direction of heat transfer in the duct: (a) If there are no shocks in the system. (b) If there is a normal shock someplace in the duct. M, = 2.0 T,- 170 K P- 0.7 bar q = ? M, = 1.0 Fig.Q4 AzlA, = 1.45arrow_forwardSparky is experimenting with using different fluids in a duct. Based on helium as the working fluid the fluid conditions upstream of a normal shock are Mach Number of 3.0, temperature of 600 ºR, and pressure of 30 psia. Determine the Mach Number, T, and p downstream of the shock. Note the figures in the textbook are based on air, not helium. The base compressible flow equations must be used with the helium ratio of specific heats of 1.667.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