NDLI: A study of the drooped leading edge airfoil. [on wind tunnel models to reduce spin entry after stall

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A study of the drooped leading edge airfoil. [on wind tunnel models to reduce spin entry after stall

Content Provider	NASA Technical Reports Server (NTRS)
Author	Anderson Jr., J. D. Barlow, J. B.
Copyright Year	1979
Description	Wind tunnel tests were conducted to examine various aspects of the drooped-leading edge airfoil which reduces the tendency for an airplane to enter a spin after stall occurs. Three baseline models were used for tests of two dimensional models: NACA 0015, 0014.6, and 0014.2. The 14.6% and 14.2% models were derived from NACA 0015 sections by increasing the chord and matching the profiles aft section. Force, balance data (lift, drag, pitching moment) were obtained for each model at a free-steam Reynold's number of 2.66 x 10 to the 6th power/m. In addition, oil flow visualization tests were performed at various angles of attack. An existing NACA 64 sub 1 A211 airfoil was used in a second series of tests. The leading edge flap was segmented in three parts which allowed various baseline/drooped leading edge configurations to be tested. Force balance and flow visualization tests were completer at chord Renolds numbers of 0.44 x 10 to the 6th power, 1.4 x 10 to the 6th power, and 2.11 x 10 to the 6th power. Test results are included.
File Size	2077643
Page Count	41
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19790017842
Archival Resource Key	ark:/13960/t0ht7f92r
Language	English
Publisher Date	1979-04-01
Access Restriction	Open
Subject Keyword	Aerodynamics Chords Geometry Airfoil Profiles Wind Tunnel Tests Flow Visualization Two Dimensional Models Wind Tunnel Models Aerodynamic Stalling Aircraft Spin Leading Edges Graphs Charts Aerodynamic Loads Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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