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Ordinates and Theoretical Pressure Distribution Data for NACA 6- and 6A-Series Airfoil Section with Thicknesses from 2 to 21 and from 2 to 15% Chord, Respectively

Basic thickness forms of the NACA 65—, 6h-, 65—series and NACA 65A-,
6hA-, 65A-series airfoil sections are tabulated for thicknesses of 2, 5,
h, and 5 percent chord. Also presented for these thin airfoil sections
are theoretical values of pressures and velocity ratios required to
obtain theoretical airfoil pressure distributions. In addition, for each
family of airfoil sections, cross plots are presented from which ordinates
and pressure distributions can be easiLy obtained for airfoil sections
of thicknesses intermediate to those presented in this report, in NACA
Report 824 (from 6 to 21 percent chord for the NACA 6—series), and in
NACA Report 903 (from 6 to 15 percent chord for the NACA 6A—series).

In order to minimize the wave drag of supersonic aircraft, the wings
and tail surfaces are designed with the use of airfoil sections thinner
than 6 percent chord. Ordinates for only a few of these thin airfoils
are published and these are not conveniently located in a single report.
This report will supplement the information presented in references 1
and 2 and provide the ordinates of additional airfoil sections useful
in design of supersonic aircraft.

The information presented in this report includes tabulated ordinates
for symmetrical NACA 6— and 6A—series airfoil sections with thicknesses
of 2, 5, h, and 5 percent chord and a simplified method of obtaining
ordinates for any thickness intermediate to published values from 2
to 21 percent chord for NACA 65-, 6h—, and 65-series and from 2 to'
15 percent chord for NACA 65A,, 6hA-, and 65A—series airfoil sections.
In addition, a stnplified procedure is presented for obtaining the
pressure distributions about airfoil sections of intermediate thicknesses.