Abstract
This paper details a quantitative investigation into a cost-effective, three degree-of-freedom test rig to determine aircraft static and dynamic stability derivatives. The technique used a specifically designed three degree-of-freedom gimbaled mechanism to connect an actively controlled model to a vertical support strut. The support strut was also mounted on a six-component piezoelectric balance to obtain aerodynamic force and moment data simultaneously with the model motion. With only minor modifications to the overall setup, a comprehensive set of static and dynamic stability derivatives were obtained which showed reasonable to good agreement with other, independently obtained, data.
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