Inside Out Library · Explore
Airfoil Section Characteristics as Affected by Variations of the Reynolds Number (1937)
NASA Technical Reports Server (NTRS) · leaf 18
14 REPORT NO. 586—NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS … .8 1.0 4.2 1.4 1.6 Angle of attach, for infinite aspect ratio, (degrees) Lift coefficient, CL Figure 20.—N, A. C. A 23021 with split flap deflected 75°. 0) 12 0 • 0 10 I- 08 .06 .04 .02 8 -.3 V Airfoil: MAC.A. 430/2 with split flap: Pres.(sfnd. atm.): I to 20 ' Tested: LMA.L, V.Q. T. 1296,1227,…NASA Technical Reports Server (NTRS)
Internet Archive · NASA Technical Reports · Public domain (US government work). Free to use for anything.
More pictures from Airfoil Section Characteristics as Affected by Variations of the Reynolds Number
More like this
