Appendix D: Linearization of a conventional aircraft model
Abstract: This section presents the linearization of a conventional aircraft model to provide a baseline for comparison with the results presented in Chapter 5. The aircraft chosen was the single-seat fighter F-16 Fighting Falcon, which has a nominal 9279 kg mass and 9.96 m wing span. A nonlinear dynamics model is contained within SIDPAC, and is documented in references [37, 2, 86].
Key Words: linearization, central finite differences, conventional aircraft
The aircraft was set at a 3048 m altitude and a 0.09 rad pitch angle. A modified Newton-Raphson algorithm was then used to solve (5.2) for the remaining trim states, which were a 137 m/s airspeed, a 19.5% throttle setting, and a ...
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