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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]
Valuesof(pc:,p/;)gdofo'typicalwingplanform-s toestimate(/;):
} general method is available U
Forsupersoni ';e;lis;er:oin9Datcomlcalculationswereperformedforq/
Usingtheinformationg entedinFig.4.26.
wing planforms and are presenr
.'.
:,
F;
.:
;u
t::
p:
c
\w.
fr
.-
P :.
. .'
'-L
406 PERFORMANCE, STABILrFY, DYNAMICS, AND CONTROL
Taper Ratio = 0.5
A, deg
~ A=2
--N- A=4
~.-.- A = 6
Taper Ratlo = 0.25
-0.1
p~ -0.3
-0.4
Taper Ratlo ~ 1.0
┏━━━━━━━━━━━━━━━━━━━━━━━━┓
┃ ┃
┣━━━━━━━━━━━━━━━━━━━━━━━━┫
┃ "" "" " " " ".... ┃
┃~ ┃
┃- - - - - f- ┃
┃-:: :::-::-:=--'- .-.::.. . - ┃
┗━━━━━━━━━━━━━━━━━━━━━━━━┛
o 20 40 60
A, deg
Fig.4.25 The parameter (pcrplk)cL=o at subsoruc speeds.;
Estimation of qp. This derivativeis a measure ofthe rolling momentinduced
due to a roll rate experienced by the aircraft and is called the damping-in-roll
derivative. This is one of the most import.ant lateral-directional dynamic deriva-
tives. The major contribution comes from the wing and the v. ertical tail, and the
contributions of the fuselage and horizontal tail are usually small and can be ig-
nored. However, the contribuOon of the horizontal tail can become significant ifit
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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL2(149)
