Further studies on the 21% thick, supercritical NLF airfoil NAE 68-060-21:1

Title

Further studies on the 21% thick, supercritical NLF airfoil NAE 68-060-21:1

 Author

Khalid, .
Jones, D.J.

Institution

National Research Council Canada, National Aeronautical Establishment

 Date

1986-09-30

 Abstract

Further wind tunnel tests have been carried out on the NAE 10" chord supercritical NLF airfoil NAE 68-060-21:1. This airfoil in previous tests showed very low drag levels when free transition was allowed on the model. In the main part of the current investigation, performed at chord Reynolds number of about 7,9 and 13 million, transition was fixed at 7% and 15% on upper and lower surfaces respectively. It is observed that there is a substantial loss of lift under these conditions which appears to be associated with boundary layer thickening on the lower surface causing decambering near the trailing edge. Also additional tests were carried out under free transition at other Reynolds numbers than those previously used. The same drag bucket behaviour near the design flow conditions was observed.

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 Publisher

National Research Council Canada

 Access restriction

Campus only

 Source

National Aeronautical Establishment, Aeronautical Note NAE-AN-41, NRC no 26453

 Part of collection

Aerospace Engineering Reports

 Document type

report

 Rights

(c) 1986 National Research Council Canada
Files
PDF NAE-AN-41.pdf 4.26 MB
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