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THE q DERIVATIVES (Cw Cm,, Che)
These derivatives represent the aerodynamic effects that accompany rotation of the airplane about a spanwise axis through the C. G. while a remains zero. An example of this kind of motion was treated in Sec. 6.10 (i. e. the steady pull-up). Figure 7.116 shows the general case in which the flight path is arbitrary. This should be contrasted with the situation illustrated in Fig. 7.11«, where q = 0 while a is changing.
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Fie. 7.11 (a) Motion with zero q, but varying a. (6) Motion with zero a, bat varying q. |
Both the wing and the tail are affected by the rotation, although, when the airplane has a tail, the wing contribution to CL and Cm^ is often negligible in comparison with that of the tail. In such cases it is common practice to increase the tail effect by an arbitrary amount, of the order of 10%, to allow for the wing and body.
