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┃ . -: --:-- ┃ ┃ ┃
┣━━━━━━━━━━━━━━━━━━━━┻━━━┻━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━┫
┃.1 0.2 0.3 0.4 0*5 0.6 0.7 0.8 0.9 .' ┃
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2bL
b
Fig 432 The parameter (trp)WB at subsonicspeeds/
The calculated values of Cmq at subsoruc and supersonic speeds are shown in
Fig. 4.33b.
CLn: Because the given configuration is tailless, we have CIA, - (CLtr)WB, which
is given by Eq. (4.527). The term (Cr.&)e was evaluated at subsonic speeds using
Eq. (4.528) and Datcom data/ at supersonic speeds. The body contribution was
evaluated using Eq. (4.530). The calculated values of Curt are shown in Fig. 4.34a.
Cmdl: We have Cm& - (Cm~t)Ha?, which is given by Eq. (4.539). The term (Cm t)e
was evaluated at subsonic and supersonic Mach numbers using Eq. (4.540) and
Datcom data] The body contribution was evaluated using Eq. (4.543).
The calculated values of Cm& are shown in Fig. 4.34b.
Lateral directional dynamic derrvatives.
Cyp: Wehave
C7p = (Cyp)W + (Cyp)V
For subsoruc speeds, the wing contribution was evaluated using Eq. (4.548). The
EQUATIONS OF MOTION AND ESTIMATION OF STABILITY DERIVATIVES 423
-0 -2
t!
8 _3
cr
E
O _4
a)
Alpha=4
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┃ l....r. ┃
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┃ :-'-.'- ┃
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┃- N. \/ ┃
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o 0.5
1-5 2 2.5 3 3.5 4
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