Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 10, Problem 10.7P
A convergent-divergent nozzle with an exit-to-throat area ratio of 1.616 has exit and reservoir pressures equal to 0.947 and 1.0 atm, respectively. Assuming isentropic flow through the nozzle, calculate the Mach number and pressure at the throat.
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An isentropic flow through a convergent-divergent nozzle with an exit-to-throat ratio of Ae/At = 2.2. The flow through the throat is subsonic and the exit pressure is pe = 0.967 atm. The inlet pressure is p = 1 atm. Determine the Mach number (Mt) at the Throat.
A converging -diverging nozzle
with a throat area of 0.0052 m^2 is
attached to a very large tank of air in
which the pressure is 136 kpa and
the temperature is 67 C° the nozzle
exhaust to the atmosphere with
pressure of 105 kpa if the mass flow
rate is 2 kg/s determine the exit area
and mach number at the throat . the
flow in the nozzle is isentropic
Air is flowing in a convergent nozzle. At a particular location within the nozzle the pressure is 280 kPa, the stream temperature is 345 K. and the velocity is 150 m/s.
If the cross-sectional area at this location is 9.29 x 103 m², find: (a) The Mach number at this location,
(b) The stagnation temperature and pressure.
(c) The area, pressure, and temperature at the exit where M-1.0. (d) The mass rate of flow for the nozzle.
Indicate any assumptions you may make and the source of data used in the solution.
Chapter 10 Solutions
Fundamentals of Aerodynamics
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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