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Synthesis of Lift and Pitching Moment
The total lift and pitching moment of an airplane are, in general, functions of angle of attack, control-surface angle(s), Mach number, Reynolds number, thrust coefficient, and dynamic pressure.[5] (The last-named quantity enters because of aeroelastic effects. Changes in the dynamic pressure (pV2), when all the other parameters are constant, may induce enough distortion of the structure to alter Cm significantly.) An accurate determination of the lift and pitching moment is one of the major tasks in a static stability analysis. Extensive use is made of wind-tunnel tests, supplemented by aerodynamic and aeroelastic analyses.
For purposes of estimation, the total lift and pitching moment may be synthesized from the contributions of the various parts of the airplane, that is, wing, body, nacelles, propulsive system, and tail, and their mutual interferences. Some data for estimating the various aerodynamic parameters involved are contained in Appendix B, while the general formulation of the equations, in terms of these parameters, follows here. In this chapter aeroelastic effects are not included. Hence the analysis applies to a rigid airplane.
