Explanation Write the formula of ratio of stagnation temperature to the static temperature at inlet of the nozzle. T 01 T 1 = 1 + k − 1 2 Ma 1 2 T 01 = T 1 ( 1 + k − 1 2 Ma 1 2 ) (I) Here, the inlet static temperature is T 1 , the inlet stagnation temperature is T 01 , the specific heat ratio is k , and Mach number of air at the inlet of nozzle is Ma 1 . Consider the flow is Rayleigh’s flow at the inlet. Hence, the ratio of inlet stagnation temperature to the critical (throat) stagnation temperature ( T 0 ∗ ) is 1. T 01 T 0 ∗ = 1 Here, the inlet stagnation temperature is T 02 , and the critical stagnation temperature is T 0 ∗ . Write the formula for stagnation temperature ratio of exit to inlet. T 0 2 T 01 = T 02 / T 0 ∗ T 01 / T 0 ∗ (II) Write the formula for heat transfer per unit mass ( q ) . q = c p ( T 02 − T 01 ) (III) Here, the specific heat at constant pressure is c p , the exit stagnation temperature is T 02 , and inlet stagnation temperature is T 01 . Refer Table A-34, “Rayleigh flow functions for an ideal gas with k = 1.4 ”. The Rayleigh flow function of exit stagnation temperature to the critical stagnation temperature corresponding to the exit Mach number of 1.6 is 0.8842 . T 02 T 0 ∗ = 0.8842 Refer Table A-2, “Ideal-gas specific heats of various common gases”. The specific heat ratio ( k ) of air is 1.4 and the specific heat at constant pressure is 1.005 kJ/kg ⋅ K . Conclusion: Substitute 340 K for T 1 , 1

9th Edition

ISBN: 9781264446889

Author: CENGEL

Publisher: MCG

See similar textbooks

Concept explainers

Work and Heat Transfer

It is generally related to thermal engineering which tells about the use, creation, conversion and transfer of heat energy between the systems. It is also considered that to transfer heat from one source to another, transfer of masses is also required. T…

Videos

Question

Chapter 17.7, Problem 135RP

To determine

The required heat transfer from the air in kJ/kg.

Expert Solution & Answer

Want to see the full answer?

Check out a sample textbook solution

See solution

Chapter 17.7, Problem 134RP

Chapter 17.7, Problem 136RP

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 LLF W/ CONNECT ACCESS

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 required heat transfer from the air in kJ/kg .

Solution Summary: The author explains the required heat transfer from the air in kJ/kg and the formula for stagnation temperature ratio of exit to inlet.

Concept explainers

Videos

The required heat transfer from the air in kJ/kg.

Want to see the full answer?

Chapter 17 Solutions