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This document contains stability and control derivatives estimated using computational fluid dynamics (CFD) software for an unmanned aerial vehicle (UAV) design. Longitudinal, lateral, and control derivatives are provided for the trim angle of attack, as well as derivatives for the elevator, rudder, and aileron control surfaces. Detailed results for the trim condition and zero angle of attack are attached. The root locus is also included as an attachment.

Author

Samer Jaradat

Language

EN