Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 2, Problem 2.13P
Consider the subsonic compressible flow over the wavy wail treated in Example 2.1. Derive the equation for the velocity potential for this flow as a function of x and y.
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Problem 2
An unconfined supersonic flow passes over the contoured wall shown below. The wall segment
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Mo. = 2.0
P., = 1 bar
==
A
B
R
30°
30° R
C
* Your answer is incorrect.
A nozzle for a supersonic wind tunnel is designed to achieve a Mach number of 3.0, with a velocity of 2000 m/s, and a
3
density of 1.0 kg/m in the test section. Find the temperature and pressure in the test section and the upstream
stagnation conditions. The fluid is helium.
Te = i 217
Pe=
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868.325
PO = i 387.2
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kPa
Chapter 2 Solutions
Fundamentals of Aerodynamics
Ch. 2 - Consider a body of arbitrary shape. If the...Ch. 2 - Consider an airfoil in a wind tunnel (i.e., a wing...Ch. 2 - Consider a velocity field where the x and y...Ch. 2 - Consider a velocity field where the x and y...Ch. 2 - Consider a velocity field where the radial and...Ch. 2 - Consider a velocity field where the x and y...Ch. 2 - The velocity field given in Problem 2.3 is called...Ch. 2 - The velocity field given in Problem 2.4 is called...Ch. 2 - Is the flow field given in Problem 2.5...Ch. 2 - Consider a flow field in polar coordinates, where...
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- Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2(2116 lb/ft2), respectively. Consider the flow field over a circular cylinder mounted perpendicular tothe flow in the test section of a low-speed subsonic wind tunnel. Atstandard sea level conditions, if the flow velocity at some region of theflow field exceeds about 250 mi/h, compressibility begins to have an effectin that region. Calculate the velocity of the flow in the test section of thewind tunnel above which compressibility effects begin to become important, i.e., above which we cannot accurately assume totallyincompressible flow over the cylinder for the wind tunnel tests.arrow_forwardB5arrow_forwardThe stagnation chamber of a wind tunnel is connected to a high-pressure air bottle farm which is outside the laboratory building. The two are connected by a long pipe of 4-in inside diameter. If the static pressure ratio between the bottle farm and the stagnation chamber is 10, and the bottle-farm static pressure is 100 atm, how long can the pipe be without choking? Assumeadiabatic, subsonic, one-dimensional flowarrow_forward
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