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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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