Assuming lifting line theory, expressions for velocity induced by walls at points along span of wing are derived for symmetrical airfoils with arbitrary lift distribution; calculations extended to unsymmetrical airfoils and to airfoils placed above or below center line of tunnel. Supplement to Report AR-7. (See Engineering Index 1951 p 1299).
Wall interference in wind tunnels of closed rectangular section: development of equations
Canada. Nat Research Council -- Aeronautical Report
1951
26 pages
Report
English
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