The Flow About a Section of a Finite-Aspect-Ratio NACA 0018 Airfoil on a Transonic Bump
Abstract
Pressure distributions on a semi span rectangular wing model having an NACA 0015 airfoil section and a moderate aspect ratio were measured at one spanwise station in tests made on a transonic bump in the Ames 16-foot high-speed wind tunnel. The free-stream Mach number range was from 0.4 to 1.06. The results showed that at a fixed angle of attack a region developed over the airfoil wherein the Mach number at each point remained essentially constant as the free-stream Mach number was increased above the critical. This region covered essentially the whole chord of the airfoil at free-stream Mach numbers near unity.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1953
- Accession Number
- ADA377534
Entities
People
- Jack A. Mellenthin
Organizations
- National Aeronautics and Space Administration