曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

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
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL2(149)