Aerodynamic Load Measurements over Leading-edge and Trailing-Edge Plain Flaps on a 6-Percent-Thick Symmetrical Circular-Arc Airfoil Section
Abstract
An investigation was made in the Langley two-dimensional lowturbulence tunnel at a Reynolds number of 2.1 million to determine the aerodynamic loads and moments over a 15-percent-chord droopednose flap and a 20-percent-chord plain trailing-edge flap on a 6-percent-thick synmetrical circular-arc airfoil section. Airfoil lift, flap normal-force, flap chord-force, and flap hinge-moment characteristics were determined for various deflections of the flaps either individually or in appropriate combinations. The results of the investigation indicated that the drooped-nose flap section normal-force and hinge-moment coefficients increased rapidly in a positive direction with increasing section lift coefficient; "but for a given lift coefficient, increasing the downward deflection of either flap produced negative increments. The plain trailing-edge flap section normal-force and hinge-moment coefficients are of a similar magnitude to those for a plain flap on a subsonic type of airfoil. The maximum flap normal-force and hinge-moment coefficients were, respectively, k.Jk and 2.2k for the drooped-nose flap as compared with 1-U8 and -0.6l for the plain trailing-edge flap.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 22, 1947
- Accession Number
- ADA801432
Entities
People
- Robert J. Nuber
- William J. Underwood
Organizations
- National Advisory Committee for Aeronautics