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Investigation of an Approximately 0.178-chord-thick NACA 6-series-type Airfoil Section Equipped with Sealed Internally Balanced 0.20-chord Ailerons and with a 0.05-chord Tab
Fioravante Visconti
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Abstract
Note presenting hinge-moment, lift, and drag measurements made on an approximately 0.178-chord-thick NACA 6-series-type airfoil section equipped with sealed internally balanced 0.20-chord ailerons and with a 0.05-chord tab. The purpose of the investigation was to obtain the effects of aileron contour and internal-balance chord on the aileron section hinge-moment characteristics and to determine the tab effectiveness in reducing the aileron section hinge moments.