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12     0.5334  0.6248  4.0005
13     0.5334  0.3886  4.5339
14     0.3970  0.1295  4.9987
~~ -: -::=:= = --
Table 3.2   Corrected upwash \ralues
                    for Sections 1-6
~__~-- -
   x,orxi d(:.).
 --
Section   Cre   da
  -_~~ -_--____-
1      1.16  0.14  0.084
2      1.00  0.18 . 0.108
3      0.84  0.22'  0.132
4      0.69  0.27  0.162
5      0.46  0.37  0.222
6      0.31   1.95  1.168
-:__--_--:------
Table 3.3   Downwash values forSections 7-14
 ---:  :--= --__-
Section
XI
th
1, (1- dd )
ckJ
drr
 ---_---_    -~_-_-   --_-
  7    0.124    0.062    -0.928
  8    0.373    0.187    -0.813
  9    0.560    0.280    -0.720
 10    0.684    0.342    -0.658
 11    0.809    0.404    -0.596
   12        0.933        0.467 .      ~0.533
 13    1.058    0.529    -0.471
 14    1.166    0.583    -0.417
  --:=:==:=:  ::=:-r----=:===  __~~
                              STATIC STABILITY AND CONTROL
For sections 7-14 (Table 3.3), we have from Eq. (3.10)
                 ' (l+dd )=1, (1-;1 )
or
With de]da - 0.5,
d6u  xi
d  =1, (1-;1 ) -1
         dd =0.51,-1
             da
The calculated values of deu/dct are presented in Table 3.3.
Next, we have to evaluate the integral in Eq. (3.7). We assume
f,"b;(1+aa )dx=Eb3..(1+a ):AXr
237
where N  is the number of body sections. In this case, N  -.  14. Using Table 3.4,
the sum is evaluated as follows.
t- b;.:  (1 + -,. )/ Axi  =  8.0114 fl13
            Table 3.4   Evaluation ofthe fuselageintegral
-_-          rr: -,
Section b;,m2( :.)x,, ,(.:)X,IT13
1
2
0.0423
0.2764
0.6161
1.0428
1.5050
1.6386
1.6386
1.5050
1.1543
0.9366
0.7154
0.3902
0.1510
0.0168
1.084
1.108
1*132
1.162
1.222
2.168
0.062
0.187
0.280
0.342
0.404
0.467
0.529
0.583
0.6149
0.5334
0.5334
0.5334
1.0668
1.0668
1.0668
1.0668
0.5334
0.5334
0.3334
0.5334
0.5334
0*3970
0.0282
0.1633
0.3720
0.6464
1.9620
3.7897
0.1084
0.3002
0.1724
0.1708
0.1541
0.0972
0.0426
0.0039
 3
 4
 5
 6
 7
 8
 9
10
11
12
13
14
238            PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
Then,
Cmcr.f = 2S  [,"bf (1+ aa  )dx
= 2S tb;.,(l+aa  ):Ax,
          1C
= 2~25-.76-. / 30~5-. . 7)8.0114
- 0.0028/deg
                                          Example 32
   Consider the generic tailless vehicle shown in Fig. 3.58/ We will be using this
vehicle as an example to illustrate the application of the methods of estimat-
ing stability and control characteristics discussed in this text. We will evaluate
　
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