Airfoil Section Characteristics as Affected by Variations of the Reynolds Number (1937)
NASA Technical Reports Server (NTRS) · leaf 17
OIL SECTION CHARACTERISTICS AS AFFECTED BY VARIATIONS OF THE REYNOLDS NUMBER .24 .22 .20 0 20 40 60 80 100 ^Percent of chord .18 U % O ^.08 ^.06 0% .04 .02 O .4 0) Airfoil: N.A.CA. 23012 with split o - o flop: Dote: 8-35 ,1 -.2 Pres.fst'nd. otm.): I to 20 -.4 Size:5"x30" Vel.(ft./sec.):3l to 70… … -18 -12 -8 -4 0 4 8 /2 16 20 24 Lift coefficient, CL Angle of attack for infinite aspect ratio, ce0 (degrees) Figure 19—N. A. C. A. 23015 with split flap deflected 75°.
NASA Technical Reports Server (NTRS)
Internet Archive · NASA Technical Reports · Public domain (US government work). Free to use for anything.
