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National Advisory Committee for Aeronautics, Technical Notes - Interference of Wing and Fuselage from Tests of 1B Combinations in the NACA Variation Density Tunnel Combinations with Split Flaps

As part of the wing—fuselage interference investiga~
tion in progress in the N. A. OLA. variable— density wind
tunnel, the effects of various split- flap arrangements ap-
plied to wing-fuselage combinations were determined.
Split flaps were found to exert their influence independ»
ently of the interference, and their effects on the aeroé
dynamic characteristics of rectangular—airfoil combina~
tions appeared to be more or loss proportional to their,
exposed span lengths. The interference, moreoVer, showed
the same character with the split flaps as without them.

An extensive program of research is being conducted
in the N-A-C-A- Variable-density wind tunnel on the inter-.
ference between wing and fuselage at large values of the
Reynolds Number (references 1, 2, and 3). Reference 1
-outlined the wing—fuselage interference program and pre~
sented the initial and basic parts thereof, comprising
test results for 209 combinations that represented, to the
widest practical extent, the most important parameters-of
combination, such as: wing position relative to the fuse»
lags, wing shape, juncture shape, and fuselage shape. The
investigation was subsequently continued mainly with re~
gard to fuselage shape and comprised combinations with
round, rectangular, triangular, elliptical, and airfoil—
type fuselages.

The wide employment of split flaps in design indicat~
ed that information would be desirable concerning the ina
terferences associated with wing—fuselage combinations
having split flaps. Medium~camber or thick wing sections
are known to be less affected by the interference of a fu—
selage than small—camber or moderately thick profiles
(e.:., the N.A.C.A. 0012). In reference 3, moreover, it
appeared that the effects of adding a split flap to a
tapered wing having a thick section at the root were lit-
tle influenced by the presence of a fuselage. In the
phase of the investigation reported herein, therefore,
various.spliteflap arrangements were added to wing-fuse—
lage combinations having rectangular N.A.C.A. 0012 air—
foils, and their effects, mainly with regard to the maxi—
mum lift, were determined.7 The doScriptions in table V
of the combinations tested indicate the scope of the ex—
perimental investigation.