NACA-TN-2080

Abstract

INTRODUCTION <br>The National Advisory Committee for Aeronautics is conducting an extensive investigation of the lift and control effectiveness of various flaps and control surfaces on wings having plan forms suitable for transonic and supersonic airplanes. The ultimate objective is to obtain flap. and aileron design criterions similar to those available for wings of conventional low-speed plan forms (references 1 to 6). As part of this broad study, the lift and lateral control characteristics of an untapered low-aspect-ratio semispan wing having various amounts of sweep and equipped with 25-percent-chord unsealed plain flaps or ailerons having various spans and spanwise locations are being investigated in the Langley 300 MPH 7- by 10-foot tunnel. <br>This paper presents the results of the investigation of the unswept wing configuration having an aspect ratio of 3.13 and utilizing the 25-percent-chord control surfaces as lift flaps. Lift, drag, pitching-moment, and flap hinge-moment data were obtained through an angle-of-attack range for various flap deflections up to 60&#186;.