Characteristics of a 15-Percent-Chord and a 35-Percent-Chord Plain Flap on the NACA 0006 Airfoil Section at High Subsonic Speeds
Abstract
Wind-tunnel tests were made on 15%- and 35%-chord plain trailing-edge flaps on NACA 0006 airfoil section. Simultaneous measurements of section lift, drag, and pitching moment were made over a range of Mach numbers at various angles of attack and flap deflections. For all flap deflections, the increment of lift coefficient at 0.875 Mach number is the same as that at low speeds or greater. On thin airfoils, loss in flap effectiveness is considerably less large a large-chord flap.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 02, 1947
- Accession Number
- ADA801422
Entities
People
- Richard J. Ilk
Organizations
- National Aeronautics and Space Administration