NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
The F-18 High Alpha Research Vehicle: A High-Angle-of-Attack Testbed AircraftThe F-18 High Alpha Research Vehicle is the first thrust-vectoring testbed aircraft used to study the aerodynamics and maneuvering available in the poststall flight regime and to provide the data for validating ground prediction techniques. The aircraft includes a flexible research flight control system and full research instrumentation. The capability to control the vehicle at angles of attack up to 70 degrees is also included. This aircraft was modified by adding a pitch and yaw thrust-vectoring system. No significant problems occurred during the envelope expansion phase of the program. This aircraft has demonstrated excellent control in the wing rock region and increased rolling performance at high angles of attack. Initial pilot reports indicate that the increased capability is desirable although some difficulty in judging the size and timing of control inputs was observed. The aircraft, preflight ground testing and envelope expansion flight tests are described.
Document ID
19920024160
Acquisition Source
Armstrong Flight Research Center
Document Type
Technical Memorandum (TM)
Authors
Regenie, Victoria
(NASA Dryden Flight Research Facility Edwards, CA, United States)
Gatlin, Donald
(NASA Dryden Flight Research Facility Edwards, CA, United States)
Kempel, Robert
(PRC Kentron, Inc. Edwards, CA, United States)
Matheny, Neil
(NASA Dryden Flight Research Facility Edwards, CA, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1992
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
H-1846
NASA-TM-104253
AIAA PAPER 92-4121
NAS 1.15:104253
Meeting Information
Meeting: Biennial Flight Test Conference
Location: Hilton Head Island, SC
Country: United States
Start Date: August 24, 1992
End Date: August 26, 1992
Sponsors: American Inst. of Aeronautics and Astronautics
Accession Number
92N33404
Funding Number(s)
PROJECT: RTOP 533-02-35
Distribution Limits
Public
Copyright
Public Use Permitted.
No Preview Available