Pressure distribution tests in full-scale wind tunnel on 2:1 tapered U S A 45 airfoil equipped with 20% chord split trailing edge flaps of various spans, indicating that only relatively small increase in normal force coefficients is to be expected by extending flap span of airfoil-flap combination beyond 70% of wing span.
Full-scale span load distribution on tapered wing with split flaps of various spans
Nat Advisory Committee Aeronautics -- Tech Notes
1937
10 pages
Bibliography, 18 Supp sheets
Aufsatz (Zeitschrift)
Englisch
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Effects of full-span and partial-span split flaps on aerodynamic characteristics of tapered wing
Engineering Index Backfile | 1934
|Span load distribution for tapered wings with partial-span flaps
Engineering Index Backfile | 1937
|Span load distribution for tapered wings with partial-span flaps
TIBKAT | 1937
|