NDLI: Boundary-layer-transition measurements in full-scale flight

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Boundary-layer-transition measurements in full-scale flight

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	1958
Description	Chemical 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.
File Size	643541
Page Count	11
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19630008170
Archival Resource Key	ark:/13960/t8dg1gc71
Language	English
Publisher Date	1958-07-28
Access Restriction	Open
Subject Keyword	Supersonic Flow Boundary Layer Transition Wing Body Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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