Wind-tunnel investigation of the aerodynamic balancing of upper-surface ailerons and split flaps (1937)
NASA Technical Reports Server (NTRS) · leaf 13
s, drag coefficients and ratios of L/D at maxi- split flap are given in figure 29. mum lift, and hinge-moment coefficients for different 2.4 2.4 10 2.0 1.6 1.2 L J) .4 8 16 24 of j degrees -.002 Fiqobe 24.—Lilt and drag coefficients for wing with balanced split flap at ails F6 Aileron rigged up 10°… … wing chord. r - 0.35 balanced split flaps, the factors that appear suitable Floras 26.—Balanced upper-surface aileron and balanced split flap. Slot arrange- for a comparison of the different arrangements in this ment 4 with aileron and flap ares tested. investigation are listed in table II. A…
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