Accession Number:

ADA000809

Title:

Low Speed Wind Tunnel Test of Jet Flaps and Floating Wingtip Ailerons on a Fighter Wing.

Descriptive Note:

Final rept.,

Corporate Author:

NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA AIR VEHICLE TECHNOLOGY DEPT

Personal Author(s):

Report Date:

1974-10-17

Pagination or Media Count:

25.0

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.

Subject Categories:

  • Aerodynamics
  • Attack and Fighter Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE