Actions for Upper-surface modifications for C sub l max improvement of selected NASA 6-series airfoils

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Upper-surface modifications for C sub l max improvement of selected NASA 6-series airfoils

Author
Szelazek, C. A.
Published
Aug 1, 1979.
Physical Description
1 electronic document
Additional Creators
Hicks, R. M.
Online Version

Availability

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
The thickness of the upper surface of 64 airfoils was increased from the leading edge to the position of maximum thickness. The modifications were generated using a numerical optimization routine coupled with an aerodynamic analysis code. The type of modification presented can be used for aircraft design or for the retrofit of current aircraft to improve the stall characteristics and climb performance. The coordinates of the modified airfoils are presented with plots of the forward 45% of the profiles and pressure distributions for both the modified and unmodified sections at an angle of attack of 14 degrees.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19790021972.
Accession ID: 79N30143.
NASA-TM-78603.
A-7889.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15724824