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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
 normal to the quarter chordline. The parameter ACha/ao B2 K cy cos Ac/4  is  given
in Fig. 3.48a. HHere, B2 is a factor to account for the control surface and the balance
chord ratios as given in Fig. 3.48c, and Ka is a factor to account for the control
Ka
oz
ACh"
ao B2Ka cos Ac/4
              OI
　
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