Two-Dimensional Subsonic Experiments with an NACA 0012 Airfoil
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1973
- Accession Number
- AD0775880
Entities
People
- D. W. Chudyk
- P. A. Catlin
- R. J. Vidal
Organizations
- Calspan