Accession Number : AD0775880

Title :   Two-Dimensional Subsonic Experiments with an NACA 0012 Airfoil.

Descriptive Note : Technical rept.,


Personal Author(s) : Vidal,R. J. ; Catlin,P. A. ; Chudyk,D. W.

Report Date : DEC 1973

Pagination or Media Count : 53

Abstract : Two-dimensional tests were made with a 6-inch chord NACA 0012 section in the Calspan 8-foot Transonic Wind Tunnel to obtain section data with minimum wall interference effects. The measurements included three - component force data, surface pressure distributions and oil flow observations, and were made at Mach numbers ranging from 0.4 to 0.95 and at a chord Reynolds number of 1,000,000. Comparisons of the lift curve data with available theory indicate that the results are within about 1% of being two-dimensional. (Modified author abstract)

Descriptors :   *Airfoils, *Wind tunnels, Subsonic characteristics, Two dimensional flow, Wind tunnel models, Flow visualization

Subject Categories : Test Facilities, Equipment and Methods
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE