曝光台 注意防骗
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and is given by
(CW)v = (Cyp)v zl COS CL - lz
b ] (4.634)
(CnB)V = -(Cyti)V lv co.S a + Zy sina
b ] (4.635)
Example 4.10
For the tailless aircraft of Examples 3.2 and 3.8, estimate the dynamic stability
parameters at subsonic and supersoruc speeds.
So/ution.
Longitudin,al dynamic stabzVity derivatives.
CLq: Because the girren wing has
the Datcoml method to evaluate the
a low aspect ratio (Ae =2.6893), we use
wing~body contribution, which is given by
EQUATIONS OF MOTION AND ESTIMATION OF STABILITY DERIVATIVES 421
A= O, M a 0.2
A= 35:M=02
A = O, M-0.8
A = 35: M = 0.8
f
2hL
b
Fig.431 The parameter c:rpr at subsonic speedsl
Eq. (4.489). We have Se = 73.6282 m2, S - 106.0114 m2, k2 - ki = 0.89, SB,max =
8.3193 m2, and/ f = 23.2410 m.For both subsonic and supersonic sl~eds, K W(B) =
1.17. For subsonic speeds, KB(y0 = 0.285 and, at supersoruc speeds,
KBcW) = 0.0063 M2 _ 0.0645 M + 0.2362
:: :t
i; "
: :.
.t \
ri l:i{
7
';t{
1
b0
q)
T;,
s_
q>
Q
c:
b
h0
q,
~o
H
q)
c>~
c:
bq\
b0
o
'1:
8
c\
b~
Cmq: Most ofthe steps involved in calculating this derivative are similar to those
in the calculation of Cr.q. The parameter (C:q) was evaluated using Datcom data/
oN
~
bq
t4
~
bq{
t:q
~
b
PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
)kpect Ratlo 2
-- M = 0.2
-N-. M=0.8
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┃ .... ┃ l I ┃
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