Report supplements information presented previously (see reference to NACA -- TN 1368, by L.K.LOFTIN, Jr, in Engineering Index 1947 p 25), and provides ordinates of additional airfoil sections useful in design of supersonic aircraft; simplified procedure for obtaining pressure distributions about airfoil sections of intermediate thicknesses.
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
NACA -- Tech Note
1958
99 pages
Report
Englisch
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