Aircraft Dynamic Stability and Response by A. W. Babister (Auth.)

By A. W. Babister (Auth.)

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ADSR-C for aircraft dynamics and of Aircraft Dynamic Stability and 40 Response PROBLEMS 1. With a certain aircraftn in level flight, the thrust T and forward speed V = constant, where n is some constant. Show that then satisfy the relation TV X = - (n+2) C . u 2. D 2 2 The pitching moment coefficient for a wing is given by C = m and where k and a are constants. Obtain expressions for M u 3. 4. [&//( 1-V /a )] sin a M. w ea o r z nneglected, e r Verify that, when compressibility effects are the American nondimensional derivatives ^x and ^Zu i- gliding flight.

30) In practice Xq is negligible. The contributions to Zq and M q from the tailplane can be expressed more simply as follows. If OLrp is the tailplane incidence, the increment in downward force on the tailplane due to the rate of pitch q is where the suffix T refers to the tailplane. 32) = S l /S& TT the tail-volume ratio. Similarly, considering the increment in pitching moment from the tailplane due to the rate of pitch q we find 9 2 Therefore M^(tail) = -jP^Sflf and Af^(tail) = - a x VT We see that M ^ ( t a i l ) = (l /3) T '6C l'ba LT T If/o Z^(tail).

To increase the effective dihedral. For a low wing aircraft (Fig. 4 . 4 ) , the Fig. e. to decrease v the effective dihedral. Thus, to maintain the same rolling moment due to sideslip, it is necessary to give a low wing a considerably greater geometric dihedral than that for a high wing. Contribution of the fin to Lv When the aircraft is sideslipping to starboard at an angle 3 (3 is s m a l l ) , the effective incidence of the fin is 3, see Fig. 5 (if sidewash effects are neglect e d ) , and the fin contributes a side force Yp to starboard given by Aerodynamic Derivatives Fig.

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