NDLI: Natural laminar flow flight experiment

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Natural laminar flow flight experiment

Content Provider	NASA Technical Reports Server (NTRS)
Author	Steers, L. L.
Copyright Year	1981
Description	A supercritical airfoil section was designed with favorable pressure gradients on both the upper and lower surfaces. Wind tunnel tests were conducted in the Langley 8 Foot Transonic Pressure Tunnel. The outer wing panels of the F-111 TACT airplane were modified to incorporate partial span test gloves having the natural laminar, flow profile. Instrumentation was installed to provide surface pressure data as well as to determine transition location and boundary layer characteristics. The flight experiment encompassed 19 flights conducted with and without transition fixed at several locations for wing leading edge sweep angles which varied from 10 to 26 at Mach numbers from 0.80 to 0.85 and altitudes of 7620 meters and 9144 meters. Preliminary results indicate that a large portion of the test chord experienced laminar flow.
File Size	466346
Page Count	10
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19810010484
Archival Resource Key	ark:/13960/t0004zd9m
Language	English
Publisher Date	1981-02-01
Access Restriction	Open
Subject Keyword	Aerodynamics Laminar Flow Transonic Wind Tunnels Wind Tunnel Tests Supercritical Wings Tact Program F-111 Aircraft Wing Panels Leading Edges Boundary Layers Mach Number Pressure Gradients Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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