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
Description: 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.
Date: May 1948
Creator: Visconti, Fioravante
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department