Effect of Linear Spanwise Variations of Twist and Circular-Arc Camber on Low-Speed Static Stability, Rolling, and Yawing Characteristics of a 45 degrees Sweptback Wing of Aspect Ratio 4 and Taper Ration 0.6
Abstract
An investigation at low scale has been made in the Langley stab unity tunnel in order to determine the effect of linear spanwise variations of twist and circular-arc camber on the low-speed aerodynamic characteristics and static-stability and rotary-stability (rolling and yawing) derivatives of a wing of aspect ratio 4, taper ratio 0.6, and with 45 deg sweepback of the quarter-chord line. Results of the investigation indicate that twist or camber produced only small changes in the maximum lift coefficient. A combination of camber and twist was more effective than twist alone in providing an increase in the maximum lift-to-drag ratio in the moderate lift-coefficient range for the wings investigated. The variation of static longitudinal stability through the lift-coefficient range was less for the twisted wing than for the twisted and cambered or plane wing. A combination of twist and camber generally extended the initial linear range of several of the static- and rotary-stability derivatives to a higher lift coefficient and, although these effects were small, higher Reynolds numbers may result in larger effects.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1952
- Accession Number
- ADA377145
Entities
People
- Byron M. Jaquet
Organizations
- National Aeronautics and Space Administration