An Analytical Investigation of Effect of High-Lift Flaps on Take-Off of Light Airplanes
Abstract
An analytical study has been made to determine the effects of promising high-lift devices on the take-off characteristics of light (personal-owner-type) airplanes. Three phases of the problem of improving take-off performance by the use of flaps were considered. The optimum lift coefficient for take-off was determined for airplanes having loadings representative of light aircraft and flying from field surfaces encountered in personal-aircraft operation. Power loading, span loading, aspect ratio, and drag coefficient were varied sufficiently to determine the effect of these variables on take-off performance, and, for each given set of conditions, the lift coefficient and velocity were determined for the minimum distance to take off and climb to 50 feet. Existing high-lift and control-device data were studied and compared to determine which combinations of such devices appeared to offer the most suitable arrangements for light aircraft. Computations were made to verify that suitable stability, control, and performance can be obtained with the optimum devices selected when they are applied to a specific airplane. In addition, a typical mechanism to provide for actuation of the movable surfaces for both high lift and lateral control is presented. As a result of the study, a single slotted, full-span flap was selected as the high-lift device best suited for a four-place, private-owner-type airplane.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1951
- Accession Number
- ADA384008
Entities
People
- Fred E. Weick
- H. H. Cherry
- L. E. Flanagan Jr.
Organizations
- National Aeronautics and Space Administration