NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Vortex flap flight test operations, a safe approachA flight test experiment was conducted at the Langley Research Center to evaluate a wing leading-edge vortex flap concept designed for use on an aircraft with highly swept wings. The flap concept was designed as a modification to the wing leading edge of an F-106B airplane. The flight testing required operations at conditions that would exceed the structural load envelope of the basic airplane in order to acquire desired research data for the modified configuration. Accordingly, the operational envelope of the modified aircraft was incrementally expanded and real-time monitoring of airframe strains at critical wing locations was mandated to insure safety of flight. The flight tests were conducted in two phases: Phase I to establish baseline data with the unmodified wing, and Phase II to determine the effects of the vortex flap on performance, handling qualities, and flow field characteristics. This paper focuses on a description of the approach and procedures used to provide the strain-gage monitoring to insure structural integrity. Highlights of the wing modification and the overall operation are also included. Within a -year period, 110 research flights were successfully completed, providing researchers with sufficient data to assess the potential benefits ascribed to the vortex flap concept without encountering severe structural problems or mishaps.
Document ID
19930061171
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Dicarlo, Daniel J.
(NASA Langley Research Center Hampton, VA, United States)
Elliott, James R.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
April 1, 1993
Publication Information
Publication: SAFE Journal
Volume: 23
Issue: 2
Subject Category
Aircraft Design, Testing And Performance
Accession Number
93A45168
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available