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be evaluated as discussed earlier.
For subsonic speeds,
(C:d)t = - ;:;) (-., )j(C,tr)e +;C_(g) (4.541)
The function Cmo(9) can obtained using the following expression, whichis a curve
fit to Datcom datal
Cmo(9) = ( p )(0.0008 r4 _ 0.0075 r3 +0.0185 r2 +0.0128 -c - 0.0003)
(4.542)
where r = pAe, Ae is the exposed wing aspect ratio, and p = JC~7.
EQUATIONS OF MOTION AND ESTIMATION OF STABILITY DERIVATIVES 403
(C:ia)e
taper ratio=0.25
c Crna)e
- A -.0
.- A = 30o
-.. A - 45o
.. A -. 600
taper rat1o=0.5
Aspect Rat1o-.2.0
Aspect Ratia=4.0
Aspect Rati0=6.0
Fig.4.23 The parameter (C:a)e for subsonic speeds:r
For supersonic speeds] the procedure of evaluating (C:rtrcr-)e is quite involved
and is not discussed here.lnstead, using Datcod data, we have performed some
calculations and presented the data on (C:a)e for some typical wing planforms in
Fig. 4.23. As noted in the case of ccZcr.)e, the wing leading-edge sweep and wing
aspect ratio have more significantinfluence, and the wing taper ratio has very little
effect on (C:na)e.
The parameter (Cmcr)B can be evaluated as follows]
For both subsonic and supersonic speeds,
(Cmcr)B=2(C;ncr)B l.:,-,.V,,](S V,.,./,) (4.543)
where xci, Xm~, and VB1 are defined in Eqs. (4.513) and (4.514). The parameter
(C:a)B can be determined using Eqs. (4.515) and (4.517).
ECtUATtONS OF MOTION AND ESTIMATION OF STABILITY DERIVATIVES 405
--- 7L~O
---- x=o.5
-.-.. x=i.o
c J!
CL
qrP
CL
Fig.4 24 r~ie parameter (C,p/CL)C,=O,U=O at supersonic speeds:'
Furthermore,
4z * . .c =olrad (4.552)
(ACyp)r = 3 sin r i - _ s,.rl(C,p)r=o.c
b
where
k (4.553)
(Cip)r=o,c,.=o = (p~~ c =oP
. ao (4.554)
k = 27r
Here ao is the ser,tional or two_dimensionallift-curve slopesgnft~dpwing at low
subsonic speeds and can be evaluated using the methods prcs 1previously in
Chapter 3. ns aTe presented in Fig. z]
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