By A. W. Babister (Auth.)
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Extra info for Aircraft Dynamic Stability and Response
118) The equations of lateral asymmetric motion for small disturbances ad n E c form The equations of lateral asymmetric2 motion can be expressed in non-dimensional 2 Eq. ( 2 . 4 9 ) by M\p V S by multiplying Eq. ( 2 . 51) by 2 ee 9 U2/lP y e eS H a. 49) to ( 2 . 5 1 ) + yp v p Zy5 + (D+l )p p n^S + (e D+n )p z p where /\± r = -Yr 2 n \ r , r x r= - i V r/ i 3 p= -Np/iz, n > 2 x, n^ = -\i N^/i . 124) ? 125) s # ez and g , l = -L /i x then become (D + y )v y lp = -Lp/i , x and g2 ^zx^x ^zxf^x ~^zxJ^z.
8) where s is the wing semi-span (measured perpendicular to Now the lift on the chordwise strip RT and thus, from Eqs. Qe^e ^^L' Thus For simplicity we take dC^/da^ constant across the span. Then and, from Eq. ( 4 . 9) Aircraft Dynamic Stability and Response 46 Thus, using a simple strip theory, we see that, for a swept wing of large aspect ratio, the contribution to L v is composed of two parts, the first proportional to dihedral angle T and independent of the second proportional to Cjj and independent of dihedral angle.
Thus, for a high wing aircraft (Fig. 4 . e. 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.