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Unformatted text preview: Spring 2004 Uniﬁed Engineering
Fluids Problems F1 F1a. An aircraft’s wing is at zero angle of attack when all wheels are on the ground. Qualitatively describe the ﬂow b ehind the wing airfoil a short time after landing touchdown. Assume 2-D ﬂow. F1b. A short time after starting its motion at speed V , a 2-D airfoil of chord c has a
circulation �, and its starting vortex is some distance d � c downstream. The ﬂuid is
incompressible and inviscid. Determine the c� and cd of the airfoil, by convention taken
p erpendicular and parallel to the direction of travel. How do these change in time? Hint:
First determine the apparent freestream ﬂow velocity vector (magnitude and direction) seen
by the airfoil.
V � d ...
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- Fall '05