Ordinates and theoretical pressure-distribution data for NACA 6- and 6A-series airfoil sections with thicknesses from 2 to 21 and from 2 to 15 percent chord, respectively /
by Elizabeth W. Patterson and Albert L. Braslow.

Description

Main Author

Patterson, Elizabeth W.

Related Names

Braslow, Albert L.
United States. National Aeronautics and Space Administration.
Langley Research Center.

Language(s)

English

Published

[Washington, D.C., U.S. G.P.O., 1961.

Subjects

Aerofoils > Aerofoils / Research.
Drag (Aerodynamics)

Summary

Basic thickness forms of the NACA 63-, 64-, 65- series and NACA 63A-, 64A-, 65 A-series airfoil sections are tabulated for thicknesses of 2, 3, 4, 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).

Note

Cover title.

Physical Description

86 p. tabl., graph. 26 cm.

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