NDLI: Alleviation of spin-entry tendencies through localization of wing-flow separation

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Alleviation of spin-entry tendencies through localization of wing-flow separation

Content Provider	NASA Technical Reports Server (NTRS)
Author	Anderson, S. B. Kroeger, R. A. Feistel, T. W.
Copyright Year	1981
Description	Studies have been made on several wing leading-edge modifications applicable at present to single-engine light aircraft, which produce stabilizing vortices at stall and beyond. These vortices have the effect of fixing the stall pattern of the wing such that the various portions of the wing upper surface stall nearly symmetrically. The lift coefficient produced is maintained at a high level to angles of attack significantly above the stall angle of the unmodified wing, and the divergence in roll usually is reduced to a controllable level. It is hypothesized that these characteristics will help prevent inadvertent spin entry after a stall. Results are presented from recent large-scale wind-tunnel tests of a typical light aircraft, both with and without the modifications. The data indicate (hot the static stall and poststall characteristics of this aircraft, in a typical landing-approach condition, are noticeably improved when it suitable leading-edge modification is employed; and also that no appreciable aerodynamic penalties are evident in the normal flight envelope.
File Size	509366
Page Count	8
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19980202341
Archival Resource Key	ark:/13960/t9z07z70b
Language	English
Publisher Date	1981-02-01
Access Restriction	Open
Subject Keyword	Aerodynamics Aircraft Landing Flight Envelopes Lift Boundary Layer Separation Wings Vortices Approach Wind Tunnel Tests Flow Visualization Yawing Moments Roll Angle of Attack Separated Flow Light Aircraft Aerodynamic Stalling Leading Edges 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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