FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
6th Edition
ISBN: 9781265141387
Author: Anderson
Publisher: MCG
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Chapter 9, Problem 9.21P
The purpose of this problem is to explain what causes the dramatic white cloud pattern generated in the flow field over the F/A-18C Hornet shown on the cover of this hook. This problem is both a tutorial and a quantitative calculation involving the reader. We first discuss some necessary
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Problem 3: Smoke and Steam
One of the most enduring images
of the Industrial Revolution is a
steam locomotive with a large
plume of smoke and ashes
streaming from the smokestack.
To classify this flow, think of
wind on a stationary train (not a
train moving in stationary air).
Part A
Is the flow ideal or viscous and why? (<10 words)
Part B
Is the flow laminar or turbulent and why? (<10 words)
Part C
Is the flow steady or unsteady and why? (<10 words)
Part D
Is the flow uniform or nonuniform and why? (<10 words)
Engineering fluid mechanics:
pathlines, streamlines, and streaklines.
A.) If somehow you could attach a light to a fluid particle and take a time exposure, would the image you photographed be a pathline or streakline? Explain from definition of each.
4. The Wright brothers used a very thin wing on their 1903 flyer. In addition, they made extensive use of a
homebuilt wind tunnel to test their wing designs.
span, b
chord, c
Model of Wright Flyer
(a) The Wright's wind-tunnel models had chord length, c, of about 0.04 m and wing span (length) of 0.26 m.
The wind tunnel operated at approximately the same wind speed as the full-scale aircraft - about 13 m/s.
Estimate the drag (friction) of a single wind-tunnel model wing under standard conditions (o = 1.225
kg/m³, = 1.7894 x 10-³ kg/s-m). Note that the wing is mounted in the wind tunnel so that both
upper and lower surfaces are exposed to the flow.
(b) The full-scale 1903 flyer had a chord length of 1.9 m and a wing span of 12.3 m. Estimate the drag
(friction) of a single full-scale Wright flyer wing flying at 13 m/s under standard atmospheric conditions.
(c) Consider the main wing configuration, which consisted of two wing surfaces (biplane) connected by 18¹
cylindrical rods. We will…
Chapter 9 Solutions
FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
Ch. 9 - A slender missile is flying at Mach 1.5 at low...Ch. 9 - Consider an oblique shock wave with a wave angle...Ch. 9 - Equation (8.80) does not hold for an oblique shock...Ch. 9 - Consider an oblique shock wave with a wave angle...Ch. 9 - Consider the flow over a 22.2 half-angle wedge. If...Ch. 9 - Consider a flat plate at an angle of attack a to a...Ch. 9 - A 30.2 half-angle wedge is inserted into a...Ch. 9 - Consider a Mach 4 airflow at a pressure of 1 atm....Ch. 9 - Consider an oblique shock generated at a...Ch. 9 - Consider the supersonic flow over an expansion...
Ch. 9 - A supersonic flow at M1=1.58 and p1=1atm expands...Ch. 9 - A supersonic flow at M1=3,T1=285K, and p1=1atm is...Ch. 9 - Consider an infinitely thin flat plate at an angle...Ch. 9 - Consider a diamond-wedge airfoil such as shown in...Ch. 9 - Consider sonic flow. Calculate the maximum...Ch. 9 - Consider a circular cylinder (oriented with its...Ch. 9 - Consider the supersonic flow over a flat plate at...Ch. 9 - (The purpose of this problem is to calculate a...Ch. 9 - Repeat Problem 9.18, except with =30. Again, we...Ch. 9 - Consider a Mach 3 flow at 1 atm pressure initially...Ch. 9 - The purpose of this problem is to explain what...
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