Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 3, Problem 3.10P
Prove that the velocity potential and the stream function for a uniform flow, Equations
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The assembly shown consists of a weightless, rigid bar AC, pinned at B, that is attachedto the steel and aluminum rods. Initially, bar AC is in horizontal position; there is agap, Δ = 9 mm, between the lower end of the steel rod and its pin support at D.Neglecting the weight of the rods, compute their stresses when they are subjected to atemperature increase of 35°C and the lower end of the steel rod is attached to itssupport.
answers: σSt = 194.617 MPaσAl = 97.308 MPa
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3. Three cables at an ambient temperature of 75°C are connected in series. The assemblyis subjected to a total tension force P = 3.75 kN. The properties of the three cables aregiven in the provided table.a. At 100°C, what is the total elongation of the assembly?b. If the said cables are arranged in a parallel assembly, determine the stress anddeformation of each cable subjected to the same tension force given andtemperature change in (a).
Answers: (a) PSt = 96.019 kN (C) PAl = 170.789 kN (T)(b) σSt = 40.884 MPa σAl = 53.311
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A rod is composed of three segments subjected to axial loads as shown. The propertiesof each segment are given in the provided table. Determine the failure stresses of eachmaterial if the whole assembly experienced:a. A total temperature drop of 50°C and sprung 1.2 mm.b. A total temperature rise of 50°C, and assuming it is firmly attached to unyieldingsupports.Assume FS = 1.85.
ANSWERS: (a) σfail St = 356.952 MPa σfail Br = 93.126 MPa σfail Al = 91.615 MPa (b) σfail St = 320.754 MPa σfail Br = 148.912 MPa σfail Al =
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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