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Fig. 3.47 Variation of section hinge-moment coefficient with angle of attack for a
plain flap.i
STATIC STABILITY AND CONTROL
Fig. 3.46 is defined as follows:
BR -
223
(3..1 24)
The variable ao/(ao)Lrieory used in Fig. 3.47 can be obtained from Fig, 3.13. Finally,
The parameter (Chcy)tbewy presented in Fig. 3.47b refers to typical airfoil sections
with thickness ratios up to 0.15.
Data to evaluate the parameter ACha of Eq. (3.121) are presented in Figs. 3.48a-
3.48c. Note that c;, c}, and c' correspond to the values of cb, C f , and c resolved
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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL2(4)
