Preliminary wind tunnel tests of flap arrangements suitable for direct and immediate control of steepness of glide path of airplane; use for which present flaps are not satisfactory; arrangement giving maximum lift coefficient of 1.90 for all flap deflections between 25° and 80°, within which range drag of wing increased regularly to large value.
Wind-tunnel tests of wing flaps suitable for direct control of glide-path angle
Nat Advisory Committee Aeronautics -- Tech Notes
1936
5 pages
12 Supp sheets
Report
Englisch
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Wind-tunnel tests of clark Y wing having split flaps with gaps
Engineering Index Backfile | 1938
|Wind-tunnel tests of clark Y wing having split flaps with gaps
Engineering Index Backfile | 1938
|