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234
Mach Numtx r
qIP
 a
Cw
 a
qr!
 a
A = 300
A = 45o
A : 60o
Taper Ratio = 1.0
Mach Number
Fig.4 26   The parameter (C,pla)w for supersonic speeds]
and that of the left wing decreases. This difference in lift gives rise to a restoring
or a negative rolling moment and is the aerodynamic mechanism that generates
the damping-in-roll because of the wing. Using strip theory, we can approximately
estimate the magnitude of this restoring moment and the damping-in-roll derivative
(Ctp)W as follows.
       The increase in the local angle of attack of an elemental wing strip  RT of width
dy at a spanwise distance y is given by
tan cxp = Zry
(4.556)
where Uo is the flight velocity. Assuming that the roll rate p is small, we obtain
so that
N  py
ap - Uo
ai(y) = a + a'p = cy + 7jY
(4.557)
(4.558)
pctt_
  k
408              PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
dL
                                                                         
                                                                         
                                                                         
                                                                         
                                                                         
                                                                         
                                                                         
　
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