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We have Ac/4 = 36.3704 deg and A = 2.6893. Here, xa is the horizontal distance
between the wing aerodynamic center ofthe exposed wing and the center of gravity
in ter.ms of mean aerodynar/uic chord and xa > 0 if the center of gravity is aft of
the aerodynamic center. From the calculations done for Example 3.2 at M - 0.7,
we have
3367 M3 _ 0.4810 M2+0.2214 M +0.4918 (0 < M < 0.80)
-,,,) w = 0.33,
For M = 0.7, we get
- (-,,,) w = 0.5266
The center of gravity is located 15,9334 m from the leading edge of the fuselage.
From Fig. 3.58, we note that the leading edge of the exposed wing is located
STATIC STABILITY AND CONTROL
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14.1275 m from the leading edge of the fuselage. We have Cre - 8.94 m and c -
6.8072 m. Then,
xcg - 15.9334 -14.1275
Crt 8 94
- 0.2020
' x-, = (-., ) - (-,,,.),;
Cre
-. 0.2020 - 0.5266 '
- -0.3246
xa
-.. = (-,,.) (-: )
c'
- -0.3:
_ }.3246(688~~;2)
- -0.4263
~
Substitution of all these values gives
(Cnp)A.W _ 0.0608]rad
C7- :
= O.OOllldeg
The combined wing contribution because of dihedral and sweep is then given by
(CnP)wing = (-O.OOOICL +O.OO11C2)/deg
The fuselage contribution is given by
(Cnp)B,W, = [-KNKR, (SS ) (b)] 7deg
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动力机械和机身手册2(40)
