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By F. G. Irving

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2) MG = 0. Centre of Gravity 1W FIG. 1. Equilibrium conditions in steady flight. C 2 28 LONGITUDINAL STATIC STABILITY However, in order to generalize this discussion, it is more convenient to deal in force and moment coefficients rather than in actual forces and moments. As indicated in Chapter 2, the discussion is then no longer restricted to a particular size of aeroplane under specific conditions. 4) The Pitching Moment For an aeroplane with the elevator and tab held fixed, there will generally only be one value of CL at which CMG is zero.

9) are those appropriate to the prevailing conditions. e. γ-^α2δηίΗηχ, *« = -^ 0 = - K r f l 2 è? (610) which is the result given by eqn. 3). S. This result is essential to the analysis of trim curves obtained in flight, which are rarely straight lines in practice. The consequences of eqn. 10) are noticed by the pilot as a variation of stick position with speed. This is shown in the following analysis. Write dltrlm dr 1trim dCL -dîï—dëT-dïT (611) For an aeroplane in steady level flight at an equivalent airspeed K .

Under these circumstances, the stick-force will only be zero at one particular speed: at lower speeds, the pilot will have to exert a pull-force, at higher speeds a push. Now the function of the trim-tab is to enable the pilot to make the stick force zero at any desired speed. Instead of applying a moment manually to balance the elevator hinge moment, he applies an aerodynamic moment. In considering the variation of tab angle with speed to keep CH = 0, it should be remembered that the elevator is always floating freely and hence it would be expected that the relationship between tab angle and airspeed (or CL) would depend on the stick-free stability.

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