Output Error Method and Two Step Method for Aerodynamic Model Identification
2005
The authors describe an instrumentation system, the flight path reconstruction models and the aerodynamic model identification results obtained for a Cessna Citation II jet aircraft, based on actual flight test data. The CL(a) curve obtained for quasi-static environments is compared with a CFD solution that was computed using non-viscous Euler equations for a three-dimensional model of the aircraft, 1 with deviations of 2% and 6% observed for the CLa and CL0 coefficients, respectively. For the dynamic case, the same aerodynamic model structure is studied using two different identification methods: the Output Error Method and the Two Step Method. In both cases only the aircraft longitudinal dynamics are considered. A proof of match performed on a consolidated aerodynamic model showed good prediction capability.
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