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Boundary-Layer-Transition Measurements in Full-Scale FlightChemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages installed in a Fiberglas "glove" installation on one wing. Tests were conducted at speeds from a Mach number of 1.2 to a Mach number of 2.0, at altitudes from 35,000 feet to 56,000 feet. Data obtained at all angles of attack, from near 0 deg to near 10 deg, have shown that the maximum transition Reynolds number on the upper surface of the wing varies from about 2.5 x 10(exp 6) at a Mach number of 1.2 to about 4 x 10(exp 6) at a Mach number of 2.0. On the lower surface, the maximum transition Reynolds number varies from about 2 x 10(exp 6) at a Mach number of 1.2 to about 8 x 10(exp 6) at a Mach number of 2.0.
Document ID
19630008170
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Banner, Richard D. (National Advisory Committee for Aeronautics. High-Speed Flight Station Edwards, CA, United States)
McTigue, John G. (National Advisory Committee for Aeronautics. High-Speed Flight Station Edwards, CA, United States)
Petty, Gilbert, Jr. (National Advisory Committee for Aeronautics. High-Speed Flight Station Edwards, CA, United States)
Date Acquired
August 1, 2013
Publication Date
July 28, 1958
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-H58E28
Accession Number
63N18047
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
SUPERSONIC FLOW
BOUNDARY LAYER TRANSITION
WING BODY

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