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F-16XL-2 Supersonic Laminar Flow Control Flight Test ExperimentThe F-16XL-2 Supersonic Laminar Flow Control Flight Test Experiment was part of the NASA High-Speed Research Program. The goal of the experiment was to demonstrate extensive laminar flow, to validate computational fluid dynamics (CFD) codes and design methodology, and to establish laminar flow control design criteria. Topics include the flight test hardware and design, airplane modification, the pressure and suction distributions achieved, the laminar flow achieved, and the data analysis and code correlation.
Document ID
20000004183
Acquisition Source
Langley Research Center
Document Type
Technical Publication (TP)
Authors
Anders, Scott G. (NASA Langley Research Center Hampton,VA United States)
Fischer, Michael C. (NASA Langley Research Center Hampton,VA United States)
Date Acquired
September 7, 2013
Publication Date
December 1, 1999
Subject Category
Aerodynamics
Report/Patent Number
NASA/TP-1999-209683
NAS 1.60:209683
L-17733
Funding Number(s)
PROJECT: RTOP 537-07-23-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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