曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
in Fig. 3.lO.may bc used. Vafues of CNa given in Fig. 3.10 are based on maximum
frontal area of the body.
The coefficients K WcB) and KBcW) arc given in Fig. 3.17 as functions of the ratio
of body diameter to wing span. Data presented in Fig. 3.17 apply for all Mach
numbers because they are based on slender body theory.
KW(B) i.o
or
KB(W)
a
STATIC STABfLfTY AND CONTROL
185
) 7 ) 4
┏━━┳━┳━━┳━┳━┳━┳━━┳━┳━┳━━━┳━┳━━━┳━━┳━┳━━━┳━┳━┳━┳━━┳━┓
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┣━━╋━╋━━╋━╋━╋━╋━━╋━╋━╋━━━╋━╋━━━╋━━╋━╋━━━╋━╋━╋━╋━━╋━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃r ┃/ ┃
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ / ┃ ┃
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃-) ┃/ ┃f ┃ ┃7 ┃ ┃
┣━━╋━╋━━╋━╋━╋━╋━━╋━╋━╋━━━╋━╋━━━╋━━╋━╋━━━╋━╋━╋━╋━━╋━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃Kwr blj,naz
b
Fig.3.17 Lift ratios KBtW) and Kw{n) (Ref.1).
20
18
I.6
1.4
12
.6
.4
.2
o
186 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
Data for KWcB) and KBcW) of Fig. 3.17 can be approximated by the following
expressions:
KW,B,=0.1714(bb )2+0.8326(bb )+0.9974 (3.27)
KB,W,=0.7810(bb )2+1.1976(bb )+0.0088 (3.28)
S/ope of pitching-moment coefficient. The slope of wing-body pitching-
moment coefficient is given by
Cmcr.WB = (/:cg - Xac,WB)CLn.WB
where
Xc8 =. 8
Xac. WB
Xtic.WB - ---
c
(3.29)
(3.30)
(3.31)
where xcg .is the distance of the center of gravity from the leading edge of the
exposed wing root chord and x"c.}w~ is the distance of aerodynamic center of the
wing-body combination from the leading edge of the exposed wing root chord.
As said before, these disLances are considered positive aft.
From Datcom,i '
(-., )=(&rt)NC'y.N+(h.,t)W(B)Cler.W'B)+(_xw)B(W)CM,.B'W) (3.32)
CLcr.W
where CLcy.(/W) iS given by Eq. (3.24) and
C,a.W,B, = CU,KW,B,(SS ) (3.33)
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