Fluid Mechanics Fundamentals And Applications
3rd Edition
ISBN: 9780073380322
Author: Yunus Cengel, John Cimbala
Publisher: MCGRAW-HILL HIGHER EDUCATION
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Chapter 12, Problem 163P
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The correct statement.
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Consider gas flow through a converging–diverging nozzle. Of the five following statements, select the one that is incorrect: (a) The fluid velocity at the throat can never exceed the speed of sound. (b) If the fluid velocity at the throat is below the speed of sound, the diversion section will act like a diffuser. (c) If the fluid enters the diverging section with a Mach number greater than one, the flow at the nozzle exit will be supersonic. (d ) There will be no flow through the nozzle if the back pressure equals the stagnation pressure. (e) The fluid velocity decreases, the entropy increases, and stagnation enthalpy remains constant during flow through a normal shock.
Please find out the following from the given question.
1. Inlet Mach Number
2. Total pressure in MPa
3. Total Temperature in K
4. Outlet Mach Number
5. Exit Velocity in m/s
6. Area Ratio, A2/A1
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.
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Chapter 12 Solutions
Fluid Mechanics Fundamentals And Applications
Ch. 12 - What is dynamic temperature?Ch. 12 - Prob. 4PCh. 12 - Prob. 5PCh. 12 - Calculate the stagnation temperature and pressure...Ch. 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. 18P
Ch. 12 - Prob. 28PCh. 12 - Prob. 39PCh. 12 - Prob. 41EPCh. 12 - Prob. 64PCh. 12 - Air enters a converging—diverging nozzle with low...Ch. 12 - Prob. 75EPCh. 12 - Prob. 76EPCh. 12 - Prob. 78PCh. 12 - Prob. 79PCh. 12 - Prob. 80CPCh. 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. 83CPCh. 12 - Prob. 84CPCh. 12 - Prob. 85CPCh. 12 - Argon gas enters a constant cross-sectional area...Ch. 12 - Prob. 87PCh. 12 - Prob. 88PCh. 12 - Prob. 89PCh. 12 - Prob. 90EPCh. 12 - Prob. 92EPCh. 12 - Prob. 93PCh. 12 - Prob. 94PCh. 12 - Prob. 95PCh. 12 - Prob. 96PCh. 12 - Prob. 97CPCh. 12 - Prob. 98CPCh. 12 - Prob. 99CPCh. 12 - Prob. 100CPCh. 12 - Prob. 101CPCh. 12 - Prob. 102CPCh. 12 - Prob. 103CPCh. 12 - Prob. 104CPCh. 12 - Air enters a 12-cm-diameter adiabatic duct at...Ch. 12 - Air enters a 15-m-long, 4-cm-diameter adiabatic...Ch. 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 15-cm-diameter adiabatic duct with...Ch. 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. 115PCh. 12 - Prob. 116PCh. 12 - Prob. 117PCh. 12 - Prob. 118PCh. 12 - Prob. 119PCh. 12 - Prob. 120PCh. 12 - Prob. 121PCh. 12 - Prob. 122PCh. 12 - A subsonic airplane is flying at a 5000-m altitude...Ch. 12 - Prob. 124PCh. 12 - Prob. 125PCh. 12 - Prob. 126PCh. 12 - Prob. 128PCh. 12 - Prob. 129PCh. 12 - Prob. 130PCh. 12 - An aircraft flies with a Mach number Ma1=0.9 at an...Ch. 12 - Prob. 132PCh. 12 - Helium expands in a nozzle from 220 psia, 740 R,...Ch. 12 - Prob. 136PCh. 12 - Prob. 137PCh. 12 - Prob. 138PCh. 12 - Prob. 139PCh. 12 - Prob. 140PCh. 12 - Prob. 141PCh. 12 - Prob. 142PCh. 12 - Prob. 143PCh. 12 - Prob. 144PCh. 12 - Prob. 145PCh. 12 - Prob. 146PCh. 12 - Prob. 147PCh. 12 - Air is cooled as it flows through a 30-cm-diameter...Ch. 12 - Prob. 149PCh. 12 - Prob. 152PCh. 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 - Prob. 163PCh. 12 - Prob. 164PCh. 12 - Assuming you have a thermometer and a device to...
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- 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-arrow_forwardQuestion 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.arrow_forwardQUESTION 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_forward
- Air 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_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_forwardThe jet is flying at MM = 1.3, where the absolute air pressure is 25 kPakPa . A shock is formed at the inlet of the engine. Assume isentropic flow within the engine. kk = 1.40 for air. (Figure 1) Figure 1 of 1 Part A Part complete Determine the Mach number of the air flow just within the engine where the diameter is 0.6 mm. Express your answer using three significant figures.arrow_forward
- Question 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_forwardAir 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_forward
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