NASA NACA-RM-L56A10

Abstract

INTRODUCTION <br>An investigation is being made by the National Advisory Committee for Aeronautics to study the characteristics of various high-lift devices on a full-scale 45O sweptback wing. One-fifth scale tests of the double slotted- flap designs proposed for tests at full scale were made in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of the flaps on the longitudinal aerodynamic characteristics of the sweptback wing. The wing had an aspect ratio of 3.7, symmetrical sections, a taper ratio of 0.41, and an average stream wise thickness ratio of 0.086. <br>In order that the design of the double slotted flaps developed in the small-scale tests can be used in the full-scale tests, the same span of flap (0.35 semispan) and the same forward limit of space for retraction (0.735 wing chord line) were used. Two double-slotted-flap configurations were used. For one, a ratio of vane chord to flap chord of existing two dimensional data (ref. 1). The flap, rearward of the vane, was 0.213 wing chord. For the other design, a smaller vane (0.266 flap chord), fixed to the flap, was chosen because it would require a less complicated retracting mechanism. <br>For comparison with the double-slotted-flap characteristics, the characteristics of a single-slotted-flap was simulated by blocking either of the slots, and the extended plain flap by blocking both slots.