Fluid Mechanics: Fundamentals and Applications
4th Edition
ISBN: 9781259696534
Author: Yunus A. Cengel Dr., John M. Cimbala
Publisher: McGraw-Hill Education
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Chapter 12, Problem 137P
To determine
Required heat transfer per unit mass.
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Consider an aircraft engine operating at subsonic conditions with a nozzle that has an exit area of 142in2 and a nozzle inlet/exit area ratio of 2. Engine gases flowing at 30lbm/s enter the nozzle with a pressure of 0.83 bar and avelocity of 144 m/s. The gases expand through the nozzle, exiting at the ambient pressure of 7.25 psia with a velocity of 1320 ft/s.
a) For these conditions, what is the force (in units of lbf) trasmitted to the structure holding the nozzle. Provide both direction and magnitude of the force.
b) Based on your results, comment on whether the force acting on the nozzle would hlep speed up or slow down a vehicle that used this nozzle as part of a jet propulsion system.
I mostly wanted help in part b. Thank you.
Air at 14 psia, 40°F, and a Mach number of 2.0 is forced to turn upward by a ramp that makes an 8° angle off the flow direction. As a result, a weak oblique shock forms. Determine the wave angle, Mach number, pressure, and temperature after the shock.
1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2.
In the reservoir of a supersonic wind tunnel, the velocity is negligible, andthe temperature is 1000 K. The temperature at the nozzle exit is 600 K.Assuming adiabatic flow through the nozzle, calculate the velocity atthe exit.
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...
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- 1- An ideal gas with k = 1.4 is flowing through a nozzle such that the Mach number is 2.4 where the flow area is 25 cm2. Assuming the flow to be isentropic, determine the flow area at the location where the Mach number is 1.2arrow_forwardAs an airplane flying with constant velocity moves from a cold air mass into a warm air mass, how does the Mach number change? increases decreases remains the samearrow_forwardAir enters a nozzle at 200 KPa, 360 K and a velocity of 180 meter per second . Assuming isentropic or adiabatic flow, if the pressure and temperature of air at a location where the air velocity equals the speed of sound, the Mach number at the nozzle inlet is Blank 1. The properties of air are: k = 1.4; Cp = 1005 J/kg-K; R = 287 J/kg-K. ***EXPRESS YOUR ANSWER in TWO (2) DECIMAL PLACE and WITHOUT UNITS****arrow_forward
- Air flows steadily through a varying cross-sectional area duct such as a nozzle at a mass flow rate of 10 lb/s. The air enters the duct at a pressure of 200 lb/in2 and 445°F with a low velocity, and it expands in the nozzle to an exit pressure of 30 lb/in2. The duct is designed so that the flow can be approximated as isentropic. Determine the density, velocity, flow area, and Mach number at each location along the duct that corresponds to an overall pressure drop of 30 lb/in2.arrow_forward1- Air enters a nozzle at 0.2 MPa, 350 K, and a stagnation velocity. Assuming isentropic flow, determine the pressure and temperature of air at a location where the air velocity equals the speed of sound. What is the ratio of the area at this location to the entrance area?arrow_forwardAn ideal gas with k = 1.4 is flowing through a nozzle such that the Mach number is 1.6 where the flow area is 45 cm2. Approximating the flow as isentropic, determine the flow area at the location where the Mach number is 0.8.arrow_forward
- Air enters a nozzle at 0.5 MPa, 420 K, and a velocity of 110 m/s. Approximating the flow as isentropic, determine the pressure and temperature of air at a location where the air velocity equals the speed of sound. What is the ratio of the area at this location to the entrance area?arrow_forwardA jet plane travels in air at pressure of 101.325 kPa and 10°C at a speed of 2000 kph. Based on the sonic velocity, the type of flow is Blank 1.arrow_forwardAt the inlet to an axial diffuser the velocity of the approaching air is 420 m/s, the stagnation pressure is 300 kPa, and the stagnation temperature is 600 K. At exit the stagnation pressure is 285 kPa and the static pressure 270 kPa. Using compressible flow analysis, determine(i) the static temperature, static pressure, and Mach number at inlet and the diffuser efficiency;(ii) the Mach numbers at exit and entry.For air take γ ¼ 1.376 and R ¼ 287 J/(kg K).arrow_forward
- Question B2 A civilian aircraft is flying at a Mach number of 0.8 at an altitude where the ambient pressure and temperature are 26.5 kPa and 223 K, respectively. The aircraft is equipped with two simple turbojet engines. The stagnation temperature at the entrance to their nozzles is 1200K and remains unchanged. You may assume the nozzles are operating under ideal conditions and the properties of hot gases leaving the nozzles are the same as air. 1- Under certain operating conditions each engine produces a gross thrust of 50×10³ N with an exit velocity of 600 m/s. For each nozzle determine its mass flow rate, exit area and the corresponding stagnation pressure at its entrance. 2- For a fuel to air ratio of 0.02, determine the net thrust of each engine corresponding to the above (part 1) operating condition. 3- What should be the minimum supply pressure to the nozzles if they were operating at choked condition? Then determine the gross thrust of each nozzle. 4- Show that for a choked…arrow_forwardin an isentropic manner, 19.6 m^3/min of air are compressed from 233.14 K and 283.82 kPa to 1306.56 kPa. Determine the power required in kWarrow_forwardAir enters a converging–diverging nozzle at 1.2 MPa with a negligible velocity. Approximating the flow as isentropic, determine the back pressure that would result in an exit Mach number of 1.8.arrow_forward
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