Page 226 - Aerodynamics for Engineering Students
P. 226
Two-dimensional wing theory 209
air speed U. A vortex of strength rV is located at (x,, yv). Show that the distribution,
k(x), of vorticity along the aerofoil from x = 0 to x = c satisfies the integral equation
where x = x1 is a particular location on the chord of the aerofoil. If x, = c/2 and
yv = h >> xv show that the additional increment of lift produced by the vortex (which
could represent a nearby aerofoil) is given approximately by
417
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37rh2 '
