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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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.
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
Chapter 10 Solutions
Fundamentals of Aerodynamics
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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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- An aircraft flies with a Mach number Ma1=0.962 at an altitude of 7062 m where the pressure is 46.2 kPa and the temperature is 246.2 K. Calculate the stagnation properties (static temperature, pressure, density), cross-section areas A1 and A2=? at the inlet and outlet of the diffuser. The diffuser at the engine inlet has an exit Mach number of Ma2=0.3. For a mass flow rate of 36,2 kg/s, determine the static pressure rise across the diffuser and the exit area. Solve the problem by making the necessary assumptions and drawing the schematic figure.arrow_forwardAir flows through a long, isentropic nozzle. The temperature and pressure at the * reservoir are 1000K and 20 atm, respectively. If the Mach number at the entrance is 0.2, determine the gas velocity at the entrance. 634 m/s 127 m/s 478 m/s 254 m/s For a large centrifugal pump, the required net positive suction head is typically around 5 ft 2 ft 15 ftarrow_forwardAsap.. 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.arrow_forward
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- For isentropic air flow through a cd nozzle shown in figure, the stagnation conditions are To=300 K and P. = I bar, the throat area is 0.1 m² and the exit area is 0.2 m². If the Mach number at throat is 0.6, calculate the velocity and the density of the air at the exit. Po 1 bar TB-300 K Throat M₁ = 0.6 exit A₁-0.1 m² A-0.2 m²arrow_forward(a) Write Area-Velocity relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (b) Write Area-density relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (c) Write Area-Mach relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (d) Plot the variation of density, pressure, temperature, velocity and Mach number for compressible flows through a supersonic Convergent-Divergent nozzle Note: Do NOT derive above relations.arrow_forwardflow angle is measured as 15.8°. Assuming the flow is isentropic, determine the e per unit frontal area, the exit Mach number and the static pressure ratio acrossarrow_forward
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