Thermodynamics: An Engineering Approach
8th Edition
ISBN: 9780073398174
Author: Yunus A. Cengel Dr., Michael A. Boles
Publisher: McGraw-Hill Education
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Chapter 17.7, Problem 40P
To determine
The lowest pressure that can be obtained at the throat of the nozzle.
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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.
1- 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?
Chapter 17 Solutions
Thermodynamics: An Engineering Approach
Ch. 17.7 - A high-speed aircraft is cruising in still air....Ch. 17.7 - What is dynamic temperature?Ch. 17.7 - Prob. 3PCh. 17.7 - Prob. 4PCh. 17.7 - Prob. 5PCh. 17.7 - Calculate the stagnation temperature and pressure...Ch. 17.7 - Prob. 7PCh. 17.7 - Prob. 8PCh. 17.7 - Prob. 9PCh. 17.7 - Prob. 10P
Ch. 17.7 - Prob. 11PCh. 17.7 - Prob. 12PCh. 17.7 - Prob. 13PCh. 17.7 - Prob. 14PCh. 17.7 - Prob. 15PCh. 17.7 - Prob. 16PCh. 17.7 - Prob. 17PCh. 17.7 - Prob. 18PCh. 17.7 - Prob. 19PCh. 17.7 - Prob. 20PCh. 17.7 - Prob. 21PCh. 17.7 - Prob. 22PCh. 17.7 - Prob. 23PCh. 17.7 - Prob. 24PCh. 17.7 - Prob. 25PCh. 17.7 - Prob. 26PCh. 17.7 - Prob. 27PCh. 17.7 - The isentropic process for an ideal gas is...Ch. 17.7 - Is it possible to accelerate a gas to a supersonic...Ch. 17.7 - Prob. 30PCh. 17.7 - Prob. 31PCh. 17.7 - A gas initially at a supersonic velocity enters an...Ch. 17.7 - Prob. 33PCh. 17.7 - Prob. 34PCh. 17.7 - Prob. 35PCh. 17.7 - Prob. 36PCh. 17.7 - Prob. 37PCh. 17.7 - Prob. 38PCh. 17.7 - Air at 25 psia, 320F, and Mach number Ma = 0.7...Ch. 17.7 - Prob. 40PCh. 17.7 - Prob. 41PCh. 17.7 - Prob. 42PCh. 17.7 - Prob. 43PCh. 17.7 - Prob. 44PCh. 17.7 - Prob. 45PCh. 17.7 - Prob. 46PCh. 17.7 - Is it possible to accelerate a fluid to supersonic...Ch. 17.7 - Prob. 48PCh. 17.7 - Prob. 49PCh. 17.7 - Consider subsonic flow in a converging nozzle with...Ch. 17.7 - Consider a converging nozzle and a...Ch. 17.7 - Prob. 52PCh. 17.7 - Prob. 53PCh. 17.7 - Prob. 54PCh. 17.7 - Prob. 55PCh. 17.7 - Prob. 56PCh. 17.7 - Prob. 57PCh. 17.7 - Prob. 58PCh. 17.7 - Prob. 59PCh. 17.7 - Prob. 62PCh. 17.7 - Prob. 63PCh. 17.7 - Prob. 64PCh. 17.7 - Prob. 65PCh. 17.7 - Air enters a nozzle at 0.5 MPa, 420 K, and a...Ch. 17.7 - Prob. 67PCh. 17.7 - Are the isentropic relations of ideal gases...Ch. 17.7 - What do the states on the Fanno line and the...Ch. 17.7 - It is claimed that an oblique shock can be...Ch. 17.7 - Prob. 73PCh. 17.7 - Prob. 74PCh. 17.7 - For an oblique shock to occur, does the upstream...Ch. 17.7 - Prob. 76PCh. 17.7 - Prob. 77PCh. 17.7 - Prob. 78PCh. 17.7 - Prob. 79PCh. 17.7 - Prob. 80PCh. 17.7 - Prob. 81PCh. 17.7 - Prob. 82PCh. 17.7 - Prob. 83PCh. 17.7 - Prob. 84PCh. 17.7 - Air flowing steadily in a nozzle experiences a...Ch. 17.7 - Air enters a convergingdiverging nozzle of a...Ch. 17.7 - Prob. 89PCh. 17.7 - Prob. 90PCh. 17.7 - Consider the supersonic flow of air at upstream...Ch. 17.7 - Prob. 92PCh. 17.7 - Prob. 93PCh. 17.7 - Prob. 96PCh. 17.7 - Prob. 97PCh. 17.7 - Prob. 98PCh. 17.7 - Prob. 99PCh. 17.7 - What is the effect of heat gain and heat loss on...Ch. 17.7 - Consider subsonic Rayleigh flow of air with a Mach...Ch. 17.7 - What is the characteristic aspect of Rayleigh...Ch. 17.7 - Prob. 103PCh. 17.7 - Prob. 104PCh. 17.7 - Air is heated as it flows subsonically through a...Ch. 17.7 - Prob. 106PCh. 17.7 - Prob. 107PCh. 17.7 - Prob. 108PCh. 17.7 - Air is heated as it flows through a 6 in 6 in...Ch. 17.7 - Air enters a rectangular duct at T1 = 300 K, P1 =...Ch. 17.7 - Prob. 112PCh. 17.7 - Prob. 113PCh. 17.7 - Prob. 114PCh. 17.7 - What is supersaturation? Under what conditions...Ch. 17.7 - Prob. 116PCh. 17.7 - Prob. 117PCh. 17.7 - Steam enters a convergingdiverging nozzle at 1 MPa...Ch. 17.7 - Prob. 119PCh. 17.7 - Prob. 120RPCh. 17.7 - Prob. 121RPCh. 17.7 - Prob. 122RPCh. 17.7 - Prob. 124RPCh. 17.7 - Prob. 125RPCh. 17.7 - Using Eqs. 174, 1713, and 1714, verify that for...Ch. 17.7 - Prob. 127RPCh. 17.7 - Prob. 128RPCh. 17.7 -
17–129 Helium enters a nozzle at 0.6 MPa, 560...Ch. 17.7 - Prob. 130RPCh. 17.7 - Prob. 132RPCh. 17.7 - Prob. 133RPCh. 17.7 - Nitrogen enters a convergingdiverging nozzle at...Ch. 17.7 - An aircraft flies with a Mach number Ma1 = 0.9 at...Ch. 17.7 - Prob. 136RPCh. 17.7 - Helium expands in a nozzle from 220 psia, 740 R,...Ch. 17.7 -
17–140 Helium expands in a nozzle from 1 MPa,...Ch. 17.7 - Air is heated as it flows subsonically through a...Ch. 17.7 - Air is heated as it flows subsonically through a...Ch. 17.7 - Prob. 145RPCh. 17.7 - Prob. 146RPCh. 17.7 - Air is cooled as it flows through a 30-cm-diameter...Ch. 17.7 - Saturated steam enters a convergingdiverging...Ch. 17.7 - Prob. 151RPCh. 17.7 - Prob. 154FEPCh. 17.7 - Prob. 155FEPCh. 17.7 - Prob. 156FEPCh. 17.7 - Prob. 157FEPCh. 17.7 - Prob. 158FEPCh. 17.7 - Prob. 159FEPCh. 17.7 - Prob. 160FEPCh. 17.7 - Prob. 161FEPCh. 17.7 - Consider gas flow through a convergingdiverging...Ch. 17.7 - Combustion gases with k = 1.33 enter a converging...
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- Compressed air from the compressor of a gas turbine enters the combustion chamber at T1 = 700 K, P1 = 560 kPa, and Ma1 = 0.2 at a rate of 0.3 kg/s. Via combustion, heat is transferred to the air at a rate of 300 kJ/s as it flows through the duct with negligible friction. Determine the Mach number at the duct exit and the drop in stagnation pressure P01 – P02 during this process. Take the properties of air to be k = 1.4, cp = 1.005 kJ/kg·K, and R = 0.287 kJ/kg·K. The Mach number at the duct exit is____ . The drop in stagnation pressure is____ kPa.arrow_forwardQUESTION 6 Air enters a diffuser with an averaged velocity of 360 m/s at a temperature of 340 kPa and 420 K and leaves at a stagnation pressure of 300 kPa with an averaged velocity of 120 m/s and a static pressure of 285 kPa. Determine, stagnation pressure and (i) the static pressure and Mach number of the air at inlet; (ii) the diffuser efficiency (iii the Mach number at exit and the overall entropy increasearrow_forwardCompressed air from the compressor of a gas turbine enters the combustion chamber at T1 = 700 K, P1 = 600 kPa, and Ma1 = 0.2 at a rate of 0.3 kg/s. Via combustion, heat is transferred to the air at a rate of 150 kJ/s as it flows through the duct with negligible friction. Determine the Mach number at the duct exit, and the drop in stagnation pressure P01 − P02 during this processarrow_forward
- A gas at a specified stagnation temperature and pressure is accelerated to Ma = 2 in a converging–diverging nozzle and to Ma = 3 in another nozzle. What can you say about the pressures at the throats of these two nozzlesarrow_forwardQuestion 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_forwardAir is expanded isentropically in a horizontal nozzle from an initial pressure of (1.0 MPa) and temperature of (800 K), to an exhaust pressure of (101 kPa). If the air enters the nozzle with a velocity of 100 m/s, determine the air exhaust velocity. Assume the air behaves as a perfect gas, with R=0.287 kJ/kg K and y = 1.4.arrow_forward
- Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.6. The pressure and temperature of air are 52 kPa and 270 K, respectively. Now, helium undergoes a normal shock under the same conditions. Calculate the entropy changes of air and helium across the normal shock. The properties of air are R = 0.287 kJ/kg-K and cp= 1.005 kJ/kg-K, and the properties of helium are R=2.0769 kJ/kg-K and cp=5.1926 kJ/kg.K. The entropy change for air is The entropy change for helium is kJ/kg-K. kJ/kg-K.arrow_forward3. A converging nozzle is fed with air from a large reservoir where the temperature and pressure are 400 K and 170 kPa, respectively. The nozzle has an exit cross - sectional area of 0.001 m2 and discharges into the atmosphere with a pressure of 100 kPa. The flow is isentropic throughout the nozzle. Determine the pressure, Mach number, temperature and velocity at the exit plane, and also find the mass flow rate. (Ans: 100 kPa, 0.9, 344.8 K, 334.8 m - s1, 0.3388 kg - s').arrow_forwardAir enters a converging-diverging nozzle with low velocity at 2.4 MPa and 120°C. If the exit area of the nozzle is 3.5 times the throat area, what must the back pressure be to produce a normal shock at the exit plane of the nozzle? The back pressure to produce a normal shock is MPa.arrow_forward
- Air enters a compressor at a stagnation state of 100 kPa and 27 ∘C. If it has to be compressed toa stagnation pressure of 900 kPa, calculate the power input to the compressor when the massflow rate is 0.02 kg s−1. Assume the compression process to be isentropic.arrow_forwardAn aircraft flies with a Mach number Ma1 = 0.9 at an altitude of 7000 m where the pressure is 41.1 kPa and the temperature is 242.7 K. The diffuser at the engine inlet has an exit Mach number of Ma2 = 0.3. For a mass flow rate of 50 kg/s, determine the static pressure rise across the diffuser and the exit areaarrow_forwardIn an ideal nozzle, the enthalpy change of the gas is 69.4 kJ/kg. Assuming the initial velocity is negligible what is the final velocity (Enter your answer to the nearest whole number of m/s)?arrow_forward
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