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 = p~2S                         (2.23)
Then,
                         D = ~p V2S[CDO + (%kV T2.)]
                                    1
                          = 2pS[CDOV2+ (%kV V; )]                (2.24)
T
coo
L
AIRCRAFT PERFORMANCE
                  cc
Fig. 23    Variation ofaerodynamic parameters with angle of attack.
Substituting V = u VR, where VR iS given by Eq. (2.15), we obtain
D = 2V~ (.2+ -,,)
Equations (2.7) and (2.8) for static performance can now be expressed as
or
and
73
(2.25)
z W     VI
Em 2g(.2+.,)_Wsiny.0   (2.26)
2zt12 _ ll4 _ t12 _ 2Em U2 sin y = O                       (2.27)
n -cosy =O
(2.28)
Equations (2.27) and (2.28) describe the static performance of the airplane for such
flight conditions as steady level fiight, steady climb, range, and endurance. Before
we discuss such probler:; of powered flights,let us consider the simple power-off
gliding flight,.
2.3  Gliding Flight
         A glideris an unpowered light airplane. The power to overcome the aerodynamic
drag comes at the expense ofits potential energy or its height above the ground.
Because a glider cannot attain the height on its own, it must be towed by another
powered airplane to the desired height and then launched to fly on its own.
    An interesting example of power-off gliding fiight is the return of the Space
Shuttle orbiter from space. The Space Shuttle orbiter glides back to the Earth and
lands on a runway like a conventional airplane.

    !
  .?
    e
 'i
 'r~
  ' ;l

 

    . -.

 

   : /:,

  . .l'

 

   1
   ''

    :.
  ',
   :
  o
 f.
   t
  t
    ::
     .
      .
   <.
     ::
     !
 :l::
     :.
      . :..
    /.
  "..

       /
   :
   :4
    .:
    . l.
  :{
   :*
     ,
   .:
  :,
    .:
        ,
      :.
  ,:
   ..
     l ':
      .
74                PERFORMANCE, STABIU-fY, DYNAMICS, AND CONTROL
Fig. 2-4    Forces acfng on a glider.
      Consider a glider fiying in a vertical plane as shown iri Fig. 2.4. Note that, for
 gliding flight, y  < O. With T : 0, Eqs. (2.7) and (2.8) reduce to the following form:
                                                  D+ W sin y - 0                                     (2.29)
                                                      L - W cos y - 0                                        (2.30)
　
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 CONTROL1(44)