A more complete citation for the A. M. O. Smith article is:
Smith, A. M. O.,"High-Lift Aerodynamics," AIAA Journal of Aircraft,
Vol. 12, No. 6, June 1975, pp. 501-530.
or
Smith, A. M. O., "High-lift aerodynamics /37th Wright Brothers Lecture"
(Douglas Aircraft Co., Long Beach, Calif.), AIAA-1974-939,
American Institute of Aeronautics and Astronautics,
Aircraft Design, Flight Test and Operations Meeting, 6th,
Los Angeles, Calif., Aug. 12-14, 1974, 44 p.
and, as I mentioned earlier, this article is reprinted in
Cebeci's book, "Legacy of a Gentle Genius." I do not know if
there are any differences among these versions or not.
There also is a good writeup here:
http://www.aoe.vt.edu/~mason/Mason_f/ConfigAeroHiLift.pdf
If you look at Figures 8.7 and 8.8 in this writeup, it seems that
leading edge devices such as slats have little effect on the lift
coefficient of the airfoil, as long as the angle of attack is
less than that required to stall the airfoil. The effect of these
devices is to enable higher angles of attack before stalling
occurs, which increases the maximum lift coefficient available.
If this is the case, you would not expect an inviscid calculation
procedure to show the effect -- you would need to calculate the
stall angle of the airfoil to see the effect of leading edge slats.
Olin Perry Norton
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