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Supersonic boundary-layer transition on the LaRC F-106 and the DFRF F-15 aircraft. Part 1: Transition measurements and stability analysisFor the case of the F-15 flight tests, boundary layer transition was observed up to Mach numbers of 1.2. For very limited and specific flight conditions, laminar flow existed back to about 20 percent chord on the surface clean up glove. Hot film instrumentation was effective for locating the region of transition. For the F-106 flight tests, transition on the wing or vertical tail generally occurred very near the attachment line. Transition was believed to be caused by either attachment line contamination or strong cross flow development due to the high sweep angles of the test articles. The compressibility analysis showed that cross flow N-factors were in the range of 5 to 12 at transition.
Document ID
19900003242
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Collier, Fayette S., Jr. (High Technology Corp. Hampton, VA., United States)
Johnson, Joseph B. (NASA Ames Research Center Moffett Field, CA., United States)
Rose, Ollie J. (PRC Kentron, Inc., Hampton VA., United States)
Miller, D. S. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1987
Publication Information
Publication: Research in Natural Laminar Flow and Laminar-Flow Control, Part 3
Subject Category
Aerodynamics
Accession Number
90N12558
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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