With the integration of the Cessna Skymaster into the TU Delft research aircraft fleet, a mathematical model is required to quantify its aerodynamic and propulsion characteristics. Aerodynamic model identification is conducted using the Two Step method applied to 19 decoupled doublet and 3-2-1-1 flight test manoeuvres. The engine model is developed as a digitised representation of coupled engine performance and propeller efficiency maps, providing corrected engine horsepower, thrust, and total pressure gain across the propeller. To support system identification, the aircraft’s centre of gravity and inertial characteristics are determined. In the absence of dedicated flight instrumentation, a method for measuring control surface deflections is devised and tested in flight. The resulting aerodynamic model demonstrates robust performance in prediction of the C_X, C_Z and C_n dimensionless forces and moment, while the C_l moment estimation remains rather weak. The engine model power estimation closely follows software predicted values.
Related dataset 4TU.ResearchData:
https://doi.org/10.4121/a74d4324-ce07-45a9-9e9a-d4177e733a0b