Explanation Air flow and deflection angle of air is shown in Figure (1). Write the expression for the Prandtl-Meyer function for upstream of air flow. ν ( Ma 1 ) = k + 1 k − 1 tan − 1 ( k − 1 k + 1 ( Ma 2 − 1 ) ) − tan − 1 ( Ma 2 − 1 ) (I) Here, Mach number of the air flow for upstream is Ma , Prandtl-Meyer function for upstream is ν ( Ma 1 ) and ratio of specific heats is k . Write the relation between deflection angle and Prandtl-Meyer function. ν ( Ma 2 ) = θ + ν ( Ma 1 ) (II) Here, Prandtl-Meyer function for downstream is ν ( Ma 2 ) , and air flow deflection angle is θ . Write the expression for the Prandtl-Meyer function for downstream of air flow. ν ( Ma 2 ) = k + 1 k − 1 tan − 1 ( k − 1 k + 1 ( Ma 2 2 − 1 ) ) − tan − 1 ( Ma 2 2 − 1 ) (III) Here, Mach number of the air flow for downstream is Ma 2 . Write the expression to calculate the downstream air pressure ( P 2 ) . P 2 = [ 1 + Ma 2 2 ( k − 1 ) / 2 ] − k / ( k − 1 ) [ 1 + Ma 1 2 ( k − 1 ) / 2 ] − k / ( k − 1 ) P 1 (IV) Here, upstream air pressure is P 1 . Write the expression to calculate the downstream air temperature ( T 2 ) . T 2 = [ 1 + Ma 2 2 ( k − 1 ) / 2 ] − 1 [ 1 + Ma 1 2 ( k − 1 ) / 2 ] − 1 T 1 (V) Here, upstream air temperature is T 1 . Conclusion: From the Table A-2a, “Ideal-gas specific heats of various common gases”, obtain the value of specific heat ratio ( k ) of air at room temperature as 1.4 . Substitute 1.4 for k , and 3.6 for Ma in Equation (I). ν ( Ma 1 ) = 1.4 + 1 1.4 − 1 tan − 1 ( 1.4 − 1 1.4 + 1 ( ( 3.6 ) 2 − 1 ) ) − tan − 1 ( ( 3

9th Edition

ISBN: 9781266084584

Author: CENGEL

Publisher: MCG

See similar textbooks

Videos

Question

Chapter 17.7, Problem 85P

To determine

The Mach number, pressure, and temperature of air after the expansion.

Expert Solution & Answer

Want to see the full answer?

Check out a sample textbook solution

See solution

Chapter 17.7, Problem 84P

Chapter 17.7, Problem 86P

Students have asked these similar questions

First monthly exam Gas dynamics Third stage Q1/Water at 15° C flow through a 300 mm diameter riveted steel pipe, E-3 mm with a head loss of 6 m in 300 m length. Determine the flow rate in pipe. Use moody chart. Q2/ Assume a car's exhaust system can be approximated as 14 ft long and 0.125 ft-diameter cast-iron pipe ( = 0.00085 ft) with the equivalent of (6) regular 90° flanged elbows (KL = 0.3) and a muffler. The muffler acts as a resistor with a loss coefficient of KL= 8.5. Determine the pressure at the beginning of the exhaust system (pl) if the flowrate is 0.10 cfs, and the exhaust has the same properties as air.(p = 1.74 × 10-3 slug/ft³, u= 4.7 x 10-7 lb.s/ft²) Use moody chart (1) MIDAS Kel=0.3 Q3/Liquid ammonia at -20°C is flowing through a 30 m long section of a 5 mm diameter copper tube(e = 1.5 × 10-6 m) at a rate of 0.15 kg/s. Determine the pressure drop and the head losses. .μ= 2.36 × 10-4 kg/m.s)p = 665.1 kg/m³

2/Y Y+1 2Cp Q1/ Show that Cda Az x P1 mactual Cdf Af R/T₁ 2pf(P1-P2-zxgxpf) Q2/ A simple jet carburetor has to supply 5 Kg of air per minute. The air is at a pressure of 1.013 bar and a temperature of 27 °C. Calculate the throat diameter of the choke for air flow velocity of 90 m/sec. Take velocity coefficient to be 0.8. Assume isentropic flow and the flow to be compressible. Quiz/ Determine the air-fuel ratio supplied at 5000 m altitude by a carburetor which is adjusted to give an air-fuel ratio of 14:1 at sea level where air temperature is 27 °C and pressure is 1.013 bar. The temperature of air decreases with altitude as given by the expression The air pressure decreases with altitude as per relation h = 19200 log10 (1.013), where P is in bar. State any assumptions made. t = ts P 0.0065h

36 2) Use the method of MEMBERS to determine the true magnitude and direction of the forces in members1 and 2 of the frame shown below in Fig 3.2. 300lbs/ft member-1 member-2 30° Fig 3.2. https://brightspace.cuny.edu/d21/le/content/433117/viewContent/29873977/View

Chapter 17 Solutions

THERMODYNAMICS: ENG APPROACH LOOSELEAF

Ch. 17.7 - A high-speed aircraft is cruising in still air....Ch. 17.7 - What is dynamic temperature?Ch. 17.7 - Prob. 3P Ch. 17.7 - Prob. 4P Ch. 17.7 - Prob. 5P Ch. 17.7 - Prob. 6P Ch. 17.7 - Calculate the stagnation temperature and pressure...Ch. 17.7 - Prob. 8P Ch. 17.7 - Prob. 9P Ch. 17.7 - Prob. 10P

Knowledge Booster

Learn more about

Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.

The Mach number, pressure, and temperature of air after the expansion.

Solution Summary: The author explains the Mach number, pressure, and temperature of air after expansion. The expression for the Prandtl-Meyer function for upstream air flow is shown in Figure (1).

Videos

The Mach number, pressure, and temperature of air after the expansion.

Want to see the full answer?

Chapter 17 Solutions