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16.100 Homework Assignment # 7
Due: Monday, November 7, 9am
Reading Assignment
Anderson, 3
rd
edition: Chapter 17, pages 787 – 801
Chapter 18, pages 803 – 810
Problem 1
In this problem, we will use Xfoil to simulate the flow of over an airfoil at relatively low
Reynolds number, and compare the results to some simple flat plate results.
To run Xfoil, you
can use
MIT server
or download a copy of Xfoil for Windows.
In either case, directions are
available on the
MIT server
.
a) Using Xfoil, calculate the drag coefficient versus Reynolds number for the NACA 0004
airfoil from
to Re
at zero degrees angle of attack.
Plot the
results on a loglog scale and include the drag coefficient from the laminar flat plate
solution by Blasius.
How does the Xfoil result compare to the flat plate theory?
3
10
1
Re
×
=
6
10
1
×
=
b) A form factor approach is often used to estimate the drag on an airfoil (or other body) by
multiplying the skin friction drag estimated from flat plate results.
Specifically, assume
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 Fall '03
 willcox
 Dynamics, Aerodynamics

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