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 8EP
To determine
Static pressure and temperature of the air in this state.
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The Airbus A-340 passenger plane has a maximum takeoff weight of about 260,000 kg, a length of 64 m, a wing span of 60 m, a maximum cruising speed of 945 km/h, a seating capacity of 271 passengers, a maximum cruising altitude of 14,000 m, and a maximum range of 12,000 km. The air temperature at the crusing altitude is about −60°C. Determine the Mach number of this plane for the stated limiting conditions.
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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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- 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) Figure Fe 50 mm 1 of 1 Determine the Mach number at section 2. Express your answer using three significant figures. M₂ = 0.768 Submit Part B T2₂ = Correct Correct answer is shown. Your answer 0.7893 was either rounded differently or used a different number of significant figures than required for this part. Determine the temperature at section 2. Express your answer using three significant figures. Submit Part C Previous Answers P2 = Submit O 15| ΑΣΦ ↓↑ vec 1 Request Answer Determine the pressure at section 2. Express your answer to three significant figures and include the appropriate units. μA Value Request Answer C Units ? ? Karrow_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_forwardAir flowing at 8 psia, 480 R, and Ma1 = 2.0 is forced to undergo a compression turn of 15°. Determine the Mach number, pressure, and temperature of the air after the compression.arrow_forward
- Determine the stagnation temperature and stagnation pressure of air that is flowing at 36 kPa, 238 K, and 295 m/s. The properties of air at room temperature are cp = 1.005 kJ/kg-K and k = 1.4. The stagnation temperature of air at this state is The stagnation pressure of air at this state is K. kPa.arrow_forwardOutside air at a temperature of 25∘C∘C is drawn into the duct and then heated along the duct at 167 kJ/kgkJ/kg. At section 1 the temperature is T� = 15∘C∘C and the absolute pressure is 98 kPakPa. Neglect friction. Determine the Mach number at section 2. Express your answer using three significant figures.arrow_forwardOutside air at a temperature of 25∘C∘C is drawn into the duct and then heated along the duct at 167 kJ/kgkJ/kg. At section 1 the temperature is T� = 15∘C∘C and the absolute pressure is 98 kPakPa. Neglect friction. Determine the Mach number at section 2. Express your answer using three significant figures.arrow_forward
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- For an ideal gas flowing through a normal shock, develop a relation for V2/V1 in terms of k, Ma1, and Ma2.arrow_forwardOutside air at a temperature of 25°C is drawn into the duct and then heated along the duct at 234 kJ/kg. At section 1 the temperature is T = 15°C and the absolute pressure is 98 kPa. Neglect friction. (Figure 1) Figure 50 mm -2 m- 1 of 1 Determine the Mach number at section 2. Express your answer using three significant figures. M₂ = 0.915 Submit Part B Correct Determine the temperature at section 2. Express your answer using three significant figures. T2₂ = 455 K Submit Part C P₂ Previous Answers Correct Determine the pressure at section 2. Express your answer to three significant figures and include the appropriate units. Submit Previous Answers Value Provide Feedback Units Previous Answers Request Answer ? * Incorrect; Try Again; 5 attempts remainingarrow_forwardAir enters a compressor with a stagnation pressure of 100 kPa and a stagnation temperature of 35°C, and it is compressed to a stagnation pressure of 900 kPa. Assuming the compression process to be isentropic, determine the power input to the compressor for a mass flow rate of 0.04 kg/sarrow_forward
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