Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 3, Problem 3.12P
Consider the flow over a semi-infinite body as discussed in Section 3.11. If
a. Draw the resulting semi-infinite body to scale on graph paper.
b. Plot the pressure coefficient distribution over the body; that is, plot
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A two-dimensional flow field has an x-component of velocity given in Cartesian coordinates by u = 2x − 3y. (a) Find v, the y-component of velocity, if the flow is incompressible and v = 0 when x = 0. (b) If the flow follows the Bernoulli equation, find an expression for the pressure distribution as a function of x and y, given that the pressure is p0 at the stagnation point.
3. A circular cylinder of radius a is fitted with two pressure sensors to measure pressure at 0 = 180° and at
150°. The intent is to use this cylinder as a stream
velocimeter, i.e. a device to determine the velocity of a
stream by measuring the pressures at the two taps. The
fluid is incompressible with a density of p.
Figure for Part (a)
U
Figure for Part (b)
30
a) Using potential flow approximation, derive a formula
for calculating U from the measured pressure
difference at the two pressure taps. Note that for
accurate measurement, the velocimeter must be
aligned to have one of the taps exactly facing the stream as shown in the figure. (Ans: 2|Aptaps|/p )
b) Suppose the velocimeter has been misaligned by ổ degrees so that the two pressure taps are now at 180°
+ 8 and 150° + 8. Derive an expression for the percent error in stream velocity measurement. Then,
calculate the error for 8 = 5°,10° and –10°. (Ans: [2/(sin2(150 + 8) – sin²(180 + 8) )– 1] × 100 )
Please find the question attached.
Chapter 3 Solutions
Fundamentals of Aerodynamics
Ch. 3 - For an irrotational flow. show that Bernoullis...Ch. 3 - Consider a venturi with a throat-to-inlet area...Ch. 3 - Consider a venturi with a small hole drilled in...Ch. 3 - Consider a low-speed open-circuit subsonic wind...Ch. 3 - Assume that a Pitot tube is inserted into the...Ch. 3 - A Pilot tube on an airplane flying at standard sea...Ch. 3 - At a given point on the surface of the wing of the...Ch. 3 - Consider a uniform flow with velocity V. Show that...Ch. 3 - Show that a source flow is a physically possible...Ch. 3 - Prove that the velocity potential and the stream...
Ch. 3 - Prove that the velocity potential and the stream...Ch. 3 - Consider the flow over a semi-infinite body as...Ch. 3 - Derive Equation (3.81). Hint: Make use of the...Ch. 3 - Derive the velocity potential for a doublet; that...Ch. 3 - Consider the nonlifting flow over a circular...Ch. 3 - Consider the nonlifting flow over a circular...Ch. 3 - Consider the lifting flow over a circular cylinder...Ch. 3 - The lift on a spinning circular cylinder in a...Ch. 3 - A typical World War I biplane fighter (such as the...Ch. 3 - The Kutta-Joukowski theorem, Equation (3.140), was...Ch. 3 - Consider the streamlines over a circular cylinder...Ch. 3 - Consider the flow field over a circular cylinder...Ch. 3 - Prove that the flow field specified in Example 2.1...
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