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By A. W. Babister (Auth.)

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43) The value of a 2 can be estimated using the Engineering NON-DIMENSIONAL FORMS OF THE AERODYNAMIC IN AMERICA Sciences Data DERIVATIVES Sheets. USED There are some important differences between the British and American notation for these derivatives. The American non-dimensional force derivatives c xu> c xa> %> z > %. c u % 2 are derived 2by direct differentiation of the non-dimensional coefficients CX (= X/{pV S) and C (= Z/\pV S) with respect to the appropriate variable (u/V , z e w/V or qc/2V ).

E. a negative rolling moment about Ox. e. 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.

R. & M. 718 (1921). 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.

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