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7
Z
CL
12 1.6 ZO 2A 28 3/ 36 +.0
pb fjmar.
Cr e
a)
z
u 1.6 ZO 24 ZB 3*2 36 4_0
pb f ~ma=
Cre
Fig.3.18 Lift ratio KBtW) at supersonic speeds.i
f _-1
r--
I
-
--
+
.,
-<
~
w
-
o
b~)
(-)
-
~
--J
g-
~
k
~6
1
=4
+
~3
u
.U ,
Q:l
-J
~1
co
X
188 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
The next task is to evaluate the parameters (Xac/Cre)N, (Xac/Cre)W(B), and (xac/
Cre)B(W), which is done as follows [note that (Xac)N, (Xoc)W(B), and (Xac)B(W) are
measured from the Ieading edge of the exposed wing root chord and are positive
aftl.
For subsonic speeds,l
(-)N =-(
Cre SB,max
xo dSb(x)
(IN - X) dx (3.36)
where Sb(x) is the local cross-sectional area of the nose, xo is the axial location of
maximum cross-sectional area, and IN iS the distance from the leading edge of the
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