Thermodynamics: An Engineering Approach
9th Edition
ISBN: 9781259822674
Author: Yunus A. Cengel Dr., Michael A. Boles
Publisher: McGraw-Hill Education
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Chapter 17.7, Problem 30P
To determine
The pressure at the throats of two different converging-diverging nozzles.
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If a flying airplane is at an altitude of 10,000 m. How would I determine the gage pressure at the stagnation point at the nose of plane with a velocity of 271 m/s.
Density of air 0.40 kg/m3.
(b) Air flows through a cylindrical duct at a rate of 2.3 kg/s. Friction between air and the
duct and friction within air can be neglected. The diameter of the duct is 10cm and the
air temperature and pressure at the inlet are T₁ 450 K and P₁ = 200 kPa. If the Mach
number at the exit is Ma2
determine the rate of heat transfer and the pressure
difference across the duct. The constant pressure specific heat of air is cp = 1.005
kJ/kg-K. The gas constant of air is R = 0.287 kJ/kg-K and assume k = 1.4.
-
1- Air flows through a device such that the stagnation pressure is 0.6 MPa,
the stagnation temperature is 4008C, and the velocity is 570 m/s. Determine
the static pressure and temperature of the air at this state.
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 - Prob. 6PCh. 17.7 - Calculate the stagnation temperature and pressure...Ch. 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 - 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. 29PCh. 17.7 - Prob. 30PCh. 17.7 - A gas initially at a supersonic velocity enters an...Ch. 17.7 - Prob. 32PCh. 17.7 - Prob. 33PCh. 17.7 - Prob. 34PCh. 17.7 - Prob. 35PCh. 17.7 - Prob. 36PCh. 17.7 - Prob. 37PCh. 17.7 - Air at 25 psia, 320F, and Mach number Ma = 0.7...Ch. 17.7 - Prob. 39PCh. 17.7 - Prob. 40PCh. 17.7 - Prob. 41PCh. 17.7 - Prob. 42PCh. 17.7 - Prob. 43PCh. 17.7 - Is it possible to accelerate a fluid to supersonic...Ch. 17.7 - Prob. 45PCh. 17.7 - Prob. 46PCh. 17.7 - Prob. 47PCh. 17.7 - Consider subsonic flow in a converging nozzle with...Ch. 17.7 - Consider a converging nozzle and a...Ch. 17.7 - Prob. 50PCh. 17.7 - Prob. 51PCh. 17.7 - Prob. 52PCh. 17.7 - Prob. 53PCh. 17.7 - Prob. 54PCh. 17.7 - Prob. 57PCh. 17.7 - Prob. 58PCh. 17.7 - Prob. 59PCh. 17.7 - Prob. 60PCh. 17.7 - Prob. 61PCh. 17.7 - Air enters a nozzle at 0.5 MPa, 420 K, and a...Ch. 17.7 - Prob. 63PCh. 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. 69PCh. 17.7 - Prob. 70PCh. 17.7 - For an oblique shock to occur, does the upstream...Ch. 17.7 - Prob. 72PCh. 17.7 - Prob. 73PCh. 17.7 - Prob. 74PCh. 17.7 - Prob. 75PCh. 17.7 - Prob. 76PCh. 17.7 - Prob. 77PCh. 17.7 - Prob. 78PCh. 17.7 - Prob. 79PCh. 17.7 - Air flowing steadily in a nozzle experiences a...Ch. 17.7 - Air enters a convergingdiverging nozzle of a...Ch. 17.7 - Prob. 84PCh. 17.7 - Prob. 85PCh. 17.7 - Consider the supersonic flow of air at upstream...Ch. 17.7 - Prob. 87PCh. 17.7 - Prob. 88PCh. 17.7 - Air flowing at 40 kPa, 210 K, and a Mach number of...Ch. 17.7 - Prob. 90PCh. 17.7 - Prob. 91PCh. 17.7 - Prob. 92PCh. 17.7 - What is the characteristic aspect of Rayleigh...Ch. 17.7 - Prob. 94PCh. 17.7 - Prob. 95PCh. 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 - Prob. 98PCh. 17.7 - Prob. 99PCh. 17.7 - Air is heated as it flows subsonically through a...Ch. 17.7 - Prob. 101PCh. 17.7 - Prob. 102PCh. 17.7 - Prob. 103PCh. 17.7 - Air enters a rectangular duct at T1 = 300 K, P1 =...Ch. 17.7 - Prob. 106PCh. 17.7 - Prob. 107PCh. 17.7 - Air is heated as it flows through a 6 in 6 in...Ch. 17.7 - What is supersaturation? Under what conditions...Ch. 17.7 - Steam enters a converging nozzle at 5.0 MPa and...Ch. 17.7 - Steam enters a convergingdiverging nozzle at 1 MPa...Ch. 17.7 - Prob. 112PCh. 17.7 - Prob. 113RPCh. 17.7 - Prob. 114RPCh. 17.7 - Prob. 115RPCh. 17.7 - Prob. 116RPCh. 17.7 - Prob. 118RPCh. 17.7 - Prob. 119RPCh. 17.7 - Using Eqs. 174, 1713, and 1714, verify that for...Ch. 17.7 - Prob. 121RPCh. 17.7 - Prob. 122RPCh. 17.7 - Prob. 123RPCh. 17.7 - Prob. 124RPCh. 17.7 - Prob. 125RPCh. 17.7 - Prob. 126RPCh. 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. 129RPCh. 17.7 - Helium expands in a nozzle from 220 psia, 740 R,...Ch. 17.7 - Helium expands in a nozzle from 0.8 MPa, 500 K,...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. 134RPCh. 17.7 - Prob. 135RPCh. 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. 138RPCh. 17.7 - Prob. 145FEPCh. 17.7 - Prob. 146FEPCh. 17.7 - Prob. 147FEPCh. 17.7 - Prob. 148FEPCh. 17.7 - Prob. 149FEPCh. 17.7 - Prob. 150FEPCh. 17.7 - Prob. 151FEPCh. 17.7 - Prob. 152FEPCh. 17.7 - Consider gas flow through a convergingdiverging...Ch. 17.7 - Combustion gases with k = 1.33 enter a converging...
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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_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_forwardCompressed 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_forward
- 4-Steam flows through a device with a stagnation pressure of 120 psia, a stagnation temperature of 7008F, and a velocity of 900 ft/s. Assuming ideal- gas behavior, determine the static pressure and temperature of the steam at this state.arrow_forwardHelium enters a converging–diverging nozzle at 0.7 MPa, 800 K, and 100 m/s. What are the lowest temperature and pressure that can be obtained at the throat of the nozzle?arrow_forwardIs it possible to accelerate a gas to supersonic velocity in a converging nozzle?arrow_forward
- how and why the stagnation enthalpy is defined? How does it differ from ordinary static enthalpyarrow_forwardAir 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_forwardQ1/ Air enters a compressor at a mass flow rate of 0.04 kg/s with a stagnation pressure of 100 kPa and a stagnation temperature of 400 °C, and it is compressed to a stagnation pressure of 900 kPa. Assuming the compression process to be adiabatic and reversible, find the power required for the compressorarrow_forward
- 5- An aircraft is flying at an altitude of (12000 m) (T = 216.65 k, P = 0.193bar) at a Mach number of (0.82). The cross-sectional area of the inlet diffuser is (0.5 m2).Determine: (a) The mass of air entering the compressor per second. (b) The speed of aircraft. (c) The stagnation pressure and temperature of air at the diffuser entry.arrow_forwardConsider a spherical tank containing compressed air. It is known from the elementary compressible theory that if a hole is opened on the tank, the compressed air will leave the tank at a mass flow rate of m. = k? where k is a constant and ? is the density at any time. Assuming an initial density ?0 and pressure P0, derive an expression for P(t).arrow_forwardA large vessel contains compressed air at To = 350 K and Po = 2 bar. A converging-diverging nozzle is attached to the vessel to discharge air. The throat area of the nozzle is 200 cm2. At the exit, the pressure is 20 kPa and the flow is supersonic. Answer the followings:arrow_forward
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