Effect of High-Lift Devices on the Static-Lateral-Stability Derivatives of a 45 deg Sweptback Wing of Aspect Ratio 4.0 and Taper Ratio 0.6 in Combination With A Body
Abstract
An investigation has been made in the Langley stability tunnel to determine the effect of high-lift devices on the low-speed static-lateral-stability derivatives of a 45 deg sweptback wing of aspect ratio 4.0 and taper ratio 0.6. Comparison between the increments in the static-lateral-stability derivatives due to flap deflection obtained from experiment and the increments evaluated by a simple sweep theory is also made. The results of the investigation show that, for moderate and high lift coefficients, an increase in trailing-edge flap span, with or without a leading-edge slat, generally resulted in increased effective dihedral and directional stability. The leading-edge slats tended mainly to extend the trends obtained at low lift coefficients for the dihedral effect to nearer maximum lift. An application of simple sweep theory and measured lift and drag increments to the evaluation of the increments in the static-lateral-stability derivatives due to trailing-edge flaps indicates that the trend and approximate magnitude of the variation of these increments with flap span are predicted in the moderate and high lift-coefficient range.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1952
- Accession Number
- ADA377046
Entities
People
- Jacob H. Lichtenstein
- James L. Williams
Organizations
- National Aeronautics and Space Administration