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National Advisory Committee for Aeronautics, Technical Notes - Tests of Three Tapered Airfoils Based on the NACA 2200, The NACA-M6, and the Clark Y Sections

Three tapered airfoils based on the N.A.C.A. 2200, the
N.A.C.A. -M6, and the Clark Y sections were tested in the
variable—density wind tunnel at a Reynolds Number of ap—
proximately 3,lO0,000. The models. which were of aspect
ratio 6, had constant chord center sections and rounded
tips, and tapered in thickness from 18 Percent at the roots
to 9 percent at the tips. The aerodynamic characteristics
are given by the usual dimensionless coefficients Plotted
for both positive and negative angles of attack and by of»
fectivo profile—drag coefficients ylottod against lift co~
efficients.

For the purpose of providing standard airfoil charac-
teristics for use in airplane design, the Hatériel Divi—'
sion of the Army Air Corps requested that six airfoils
having commonly used sections be tested in the variable»
density wind tunnel. In accordance with this request, the
six airfoils were tested and the results are given in ref~
erence 1. In order to extend the standard characteristics
to tapered wings, the Materiel Division later requested
that two of the sections, the N.A.C.A.—M6 and the Clark Y.
be used as basic sections for two tapered airfoils. The
N.A.C.A. therefore had two tapered airfoils constructed in
accordance with the following specifications: plan taper
2:1, constant chord center section of length equal to the
root chord, rounded tips, aspect ratio 6, and thickness
taper 18 percent to 9 percent. After the tests Of these~
airfoils were completed, tests of an additional tapered
airfoil based on the N.A.0.A. 2200 sections were request—
ed. This airfoil was supplied by the Consolidated Aircraft
Corporation. The airfoils are referred to in this report,
according to the basic sections, as the N.A.C.A. 2218-09,
the N.A.C.A.—M6, and the Clark Y tapered airfoils.