The Effect of End Plates on Swept Wings at Low Speed
Abstract
An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the effects of various sizes and shapes of end plates on the aileron characteristics and on the aerodynamic characteristics in pitch and yaw of a wing of aspect ratio 2 with no taper and a sweepback of 45 deg and of a wing of aspect ratio k, taper ratio 0.6, and sweepback of 46.7 deg. Free-roll characteristics were obtained with two end-plate configurations on a wing of aspect ratio 3, taper ratio 0.6, and a sweepback of 35 deg in order to determine the effect of end plates on wing damping in roll. The addition of the end plates to the swept wings increased the lift-curve slope, reduced the maximum lift-drag ratio, generally decreased the maximum lift coefficient, and increased the longitudinal stability slightly in the low lift coefficient range.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1950
- Accession Number
- ADB257846
Entities
People
- James M. Watson
- John M. Riebe
Organizations
- National Advisory Committee for Aeronautics