In the early 1980s, two F-16 airplanes were modified to extend the fuselage length and incorporate a large area delta wing planform. These two airplanes, designated the F-16XL, were designed by the General Dynamics Corporation (now Lockheed Martin Tactical Aircraft Systems) (Fort Worth, Texas) and were prototypes for a derivative fighter evaluation program conducted by the United States Air Force. Although the concept was never put into production, the F-16XL prototypes provided a unique planform for testing concepts in support of future high-speed supersonic transport aircraft. To extend the capabilities of this testbed vehicle the F-16XL ship 1 aircraft was upgraded with a digital flight control system. The added flexibility of a digital flight control system increases the versatility of this airplane as a testbed for aerodynamic research and investigation of advanced technologies. This report presents the handling qualities flight test results covering the envelope expansion of the F-16XL with the digital flight control system.
Flight Test Results for the F-16XL With a Digital Flight Control System
2004-03-01
Report
No indication
English
F-16XL flight test program overview
AIAA | 1983
|F-16XL Supersonic Laminar Flow Control Glove Flight Test Results
British Library Conference Proceedings | 1991
|SPECIAL SECTION: PREDICTION OF F-16XL FLIGHT-FLOW PHYSICS - Prediction of F-16XL Flight-Flow Physics
Online Contents | 2009
|Introduction: Prediction of F-16XL Flight Flow Physics
NTIS | 2009
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