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Wind Tunnel Investigation of an NACA 66-Series 16% Thick Low Drag Tapered Wing with Fowler and Split Flaps

An investigation was undertaken several years ago
in the Langley 19-foot pressure tunnel to obtain informa-
tion regarding the aerodynamic characteristics in three-
dimensional flow of representative wings with NACA low-
drag airfoils and various high-lift devices. Preliminary
tests were made of a low-drag tapered wing of 15-foot
span with a straight trailing edge and several arrangements
of trailing-edge flaps. A great deal of difficulty was
encountered in obtaining valid measurements of the char-
acteristics primarily because of errors in corrections
for model—support tare and interference and because of
inaccuracies of the tunnel balances. Some of the data
for the wing with split flaps were published in refer-
ence 1. Later tests of the same wing (15-foot span) and
a smaller but geometrically similar wing (12-foot span)
indicated that these data were in error for the afore-
mentioned reasons.

Recently the investigation was continued with tests
of the small (lZ-foot-span) wing to obtain data under more
favorable test conditions, namely, improved tunnel balances
and testing techniques. The wing was tested with partial-
and full-span arrangements of 0.50-chord Fbwler flaps
and 0.20-cherd split flaps.

Lift, drag, Ditching-moment, and stalling character-
istics are given in the present report. The results
supersede the data of reference 1.