NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Force and moment measurements on a 74 deg delta wing with an apex flapResults are presented of a subsonic experimental investigation of an apex flap concept on a 74 deg swept delta wing with trailing-edge flaps. The apex flap comprised approximately 6 percent of the wing area forward of a transverse hinge, allowing for upward and downward deflection angles from +40 deg to -20 deg. Upward deflection forces leading-edge vortex formation on the apex flap, resulting in an increased lift component on the apex area. The associated nose-up moment balances the nose-down moment due to trailing-edge flaps, resulting in sizeable increase in the trimmed lift coefficient particularly at low angles of attack. Nose-down apex deflection may be used to augment the pitch control for rapid recovery from high-alpha maneuvers. This report presents the balance data without analysis.
Document ID
19850002610
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Buter, T. A. (North Carolina State Univ. Raleigh, NC, United States)
Rao, D. M. (Vigyan Research Associates, Inc., Hampton Va., United States)
Date Acquired
September 5, 2013
Publication Date
October 1, 1984
Publication Information
Publisher: NASA. Langley Research Center
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-166081
NAS 1.26:166081
Accession Number
85N10918
Funding Number(s)
CONTRACT_GRANT: NCC1-46
PROJECT: RTOP 505-31-43-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available