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.3 .4 .5
(-,,: :.o Oerrad) .
M t0
Fig. 4.28 The parameter (C,r/CL)W for subsonic speeds.
The data to evaluate the parameter (Clr/CL)CL = O,M =0 are- presented in Fig. 4.28.
Furthermore,
A12 ) _ (l/2) (A +A4"oAA.,,)~rad' (4.617)
The vertical tail contribution is given by7
(Clr)V : b2(lycos a-+zysina)(zycos oc -lysina)Cyp,v (4.618)
The value of (CLr)V given by Eq. (4.618) is per radian.
For sup iic speeds, no general. method suitable for engineering purposes is
availablupersonic
Estimation of Cnr. This derivativeis a measure ofthe yawing momentinduced
due to the yaw rate experienced by the aircraft and is known as the damping-in-yaw
derivative. This is one of the most important lateral-directional dynamic stability
416 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
derivatives. Generally, the contributions of the fuselage and horizontal tail are
small and can be ignored so that
Cnr = (Cnr)W + (Cnr)V
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动力机械和机身手册2(128)
