Low Speed Wind Tunnel Test of Jet Flaps and Floating Wingtip Ailerons on a Fighter Wing.
Abstract
An 18% scale semispan fighter wing was tested at low speed in various configurations to assess improvements in lift and roll control. A full span jet flap achieved a CL 14% higher than current aircraft. Floating wingtip ailerons provided undiminished roll control up through high angles of attack. Parameters measured were angle of attack, lift coefficient, drag coefficient, pitching moment, rolling moment, and yawing moment.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 17, 1974
- Accession Number
- ADA000809
Entities
People
- John A. Eney
- Samuel Greenhaigh
Organizations
- Naval Air Warfare Center Warminster