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 76P
To determine
The stagnation pressure and Mach number before of the shock, and pressure, temperature, velocity, Mach number, and stagnation pressure after of the shock.
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Nitrogen enters a duct with varying flow area at 400 K, 100 kPa, and a Mach number of 0.3. Assuming a steady, isentropic flow, determine the temperature, pressure, and Mach number at a location where the flow area has been reduced by 20 percent.
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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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- Ahead of the normal shock wave, the upstream pressure , temperature, and Mach number are 0.53 atm, 255 K, and 2.8, respectively. Determine the pressure downstream of the shock wave.arrow_forwardNitrogen enters a converging–diverging nozzle at 620 kPa and 310 K with a negligible velocity, and it experiences a normal shock at a location where the Mach number is Ma = 3.0. Calculate the pressure, temperature, velocity, Mach number, and stagnation pressure downstream of the shock. Compare these results to those of air undergoing a normal shock at the same conditions.arrow_forwardAn ideal gas flows through a passage that first converges and then diverges during an adiabatic, reversible, steady-flow process. For supersonic flow at the inlet, sketch the variation of pressure, velocity, and Mach number along the length of the nozzle when the Mach number at the minimum flow area is equal to unity.arrow_forward
- How does the Mach number affect the behavior of compressible flow in a supersonic nozzle?arrow_forwardConsider the isentropic flow through a convergent-divergent nozzle with an exit-to-throat area ratio of 2.5. The reservoir pressure and temperature are 1 atm and 288 K, respectively. Calculate the Mach number, pressure, and temperature at both the throat and the exit for the cases where (a) the flow is supersonic at the exit and (b) the flow is subsonic throughout the entire nozzle except at the throat, where M = 1.arrow_forwardAir 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.arrow_forward
- Mach number at a certain section in a diverging part of a c-d nozzle is 0.7. At farther section (towards the exit), Mach number reduces to 0.4. Hence, the cross-sectional area of the farther section is greater byarrow_forwardAir at a total pressure and temperature of 8 atm and 450 K enters a frictionless constant cross-section duct. A heat addition of 850 kJ/kg makes the flow to choke at the duct exit, determine the inlet Mach number and the total pressure and total temperature at the exit.arrow_forwardConsider the supersonic flow of air over a two-dimensional wedge with a half angle of 10 degrees at 70 kPa, 260 kelvin, and mach number 2.4 after shock. If the axis of the wedge is tilted 25 degrees beforehand, determine the post-shock Mach number, temperature and pressure on the wedge.arrow_forward
- Consider a normal shock wave in a supersonic airstream where the pressure upstream of the shock is 1 atm. Calculate the loss of total pressure across the shock wave when the upstream Mach number is (a) M1 = 2, and (b) M1 = 4. Compare these two results and comment on their implication.arrow_forwardConsider air entering a heated duct at p1 = 1 atm and T1 = 288 K. Ignore the effect of friction. Calculate the amount of heat per unit mass (in joules per kilogram) necessary to choke the flow at the exit of the duct for an inlet Mach number of M1 = 2.2.arrow_forwardA long pipe of 0.0254 m diameter has a mean coefficient of friction of 0.003. Air enters the pipe at a mach number of 2.5, stagnation temperature 310 K and static pressure 0.507 bar. Determine for a section at which the mach number reaches 1.2: i) Static pressure and temperature, ii) Stagnation pressure and temperature, iii) Velocity of air, iv) Distance of this section from the inlet and v) mass flow rate of air.arrow_forward
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