Connect with LearnSmart for Anderson: Fundamentals of Aerodynamics, 6e
6th Edition
ISBN: 9781259683268
Author: Anderson, John
Publisher: Mcgraw-hill Higher Education (us)
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Textbook Question
Chapter 10, Problem 10.9P
Consider a convergent-divergent nozzle with an exit-to-throat area ratio of 1.53. The reservoir pressure is 1 atm. Assuming isentropic flow, except for the possibility of a normal shock wave inside the nozzle, calculate the exit Mach number when the exit pressure
(a) 0.94 atm (b) O.886 atm (c) 0.75 atm (d) 0.154 atm
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(a) Write Area-Velocity relation for compressible flows through a supersonic Convergent-Divergent nozzle
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(b) Write Area-density relation for compressible flows through a supersonic Convergent-Divergent nozzle
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(c) Write Area-Mach relation for compressible flows through a supersonic Convergent-Divergent nozzle
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(d) Plot the variation of density, pressure, temperature, velocity and Mach number for compressible flows
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Note: Do NOT derive above relations.
At some section in the convergent-divergent nozzle, in which air is flowing,
pressure, velocity, temperature and cross-sectional area are 200 kN/m², 170 m/s, 200°C and 1000
mm² respectively. If the flow conditions are isentropic, determine:
(i) Stagnation temperature and stagnation pressure, (ii) Sonic velocity and Mach number at this
section, (iii) Velocity, Mach number and flow area at outlet section where pressure is 110 kN/m²,
(iv) Pressure and temperature at throat of the nozzle. Take for air: R=287 J/kg K, cp = 1.0 kJ/kg
K and k = 1.4
A convergent-divergent
operating isentropically.
Pback
P01
= 0.8
3
nozzle has an exit Mach number of 1.8 when
If the back pressure is increased such that:
Show Transcribed Text
a shock appears in the divergent portion. What is
Aerit
Ashock
Chapter 10 Solutions
Connect with LearnSmart for Anderson: Fundamentals of Aerodynamics, 6e
Ch. 10 - The reservoir pressure and temperature for a...Ch. 10 - A flow is isentropically expanded to supersonic...Ch. 10 - A Pitot tube inserted at the exit of a supersonic...Ch. 10 - For the nozzle flow given in Problem 10.1, the...Ch. 10 - A closed-form expression for the mass flow through...Ch. 10 - Prob. 10.6PCh. 10 - A convergent-divergent nozzle with an...Ch. 10 - For the flow in Problem 10.7, calculate the mass...Ch. 10 - Consider a convergent-divergent nozzle with an...Ch. 10 - A 20 half-angle wedge is mounted at 0 angle of...
Ch. 10 - The nozzle of a supersonic wind tunnel has an...Ch. 10 - We wish to design a supersonic wind tunnel that...Ch. 10 - Consider a rocket engine burning hydrogen and...Ch. 10 - For supersonic and hypersonic wind tunnels, a...Ch. 10 - Return to Problem 9.18. where the average Mach...Ch. 10 - Return to Problem 9.19, where the average Mach...Ch. 10 - A horizontal flow initially at Mach I flows over a...Ch. 10 - Consider a centered expansion wave where M1=1.0...
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