Abstract
Wind-tunnel tests were conducted for a power-off and stick-fixed 1/12 scale model of a high-wing FAR 23 cargo transport airplane at Reynolds number 0.92 × 10 6 and Mach number 0.2. Tests included simultaneous measurements of six-component force and moment using the tunnel external balance. Effects of flap, elevator, rudder, and aileron on longitudinal and lateral-directional aerodynamics were investigated in a stability-axis system. Pertinent static stability and control derivatives were obtained and used for the analysis of airplane open-loop dynamic stability and response. The airplane in its cruise flight phase appears to achieve better than level 3 longitudinal flying qualities. Changes are suggested in size and shape of airplane components for improvement in design.
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