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By F. G. Irving

ISBN-10: 1483200191

ISBN-13: 9781483200194

ISBN-10: 1483225224

ISBN-13: 9781483225227

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4) Hence if "trim curves" such as Fig. 3 are drawn for different values of Kn their slopes will be proportional to Kn and they will pass through the same point when extrapolated to CL = 0. This feature of trim curves is often of practical value when plotting results obtained from flight tests. (See Fig. ) 56 LONGITUDINAL STATIC STABILITY In the foregoing theory, it has been assumed that the tab angle ß is constant. In practice, as the pilot changes the speed from one value to another, he will normally adjust the tab angle so that the stick-force is always zero at the trimmed speed.

E. 16) S ~a\ da/' STICK-FIXED AND STICK-FREE STABILITY 49 The stick-free static margin, from eqn. IT> The stick-free neutral point is obtained by putting K'„ = 0 in eqn. e. 18) The effective tail volume coefficient F'/(l +F) is usually denoted by VT where, from eqn. 19) where l'n is the distance from the stick-free neutral point to the aerodynamic centre of the tail. 18) may therefore be written more briefly as K = (h0-h)+VTa^l-^j, *i = Äo + F r ^ ( l - ^ ) . g. g. margin", and is equal to the stick-free static margin under the assumed conditions.

4. Curves of elevator angle-to-trim as a function of lift coefficient at two values of the static margin. In obtaining eqn. g. position. In fact, it is not necessary to make such assumptions and it is useful to prove this relationship under more general conditions. Suppose that the aeroplane is initially in trim at a lift coefficient CL. Since the pitching moment must be zero, eqn. 9) will become CMG = 0 = CMo + (fc-ft 0 )C L - V'CLT. 5) If the lift coefficient is now altered by <5CL, the elevator angle being kept constant, an out-of-balance pitching moment coefficient ÖCMG will result.

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An Introduction to the Longitudinal Static Stability of Low-Speed Aircraft by F. G. Irving


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