Tests made in NACA 4 by 6-ft vertical tunnel; section data suitable for application to design of horizontal and vertical tail surfaces were obtained.
Pressure-distribution investigation of N.A.C.A. 0009 airfoil with 80-percent-chord plain flap and three tabs
Nat Advisory Committee Aeronautics -- Tech Note
1940
11 pages
23 Supp plates, Bibliography
Report
English
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Engineering Index Backfile | 1940
|Engineering Index Backfile | 1939
|