NACA-RM-L50F16

Abstract

INTRODUCTION <br>The use of sweep t o delay the effects of compressibility on the aerodynamic characteristics of airplane wings has given rise to a need for h t a on swept wings at both low and high speeds to aid designers in their evaluation of wing characteristics. Previous investigations, references 1 and 2, for instance, have indicated pronounced scale effects on the characteristics of swept wings with other than sharp leading edges. It is desirable, therefore, that data for these wings should be obtained at Reynolds numbers as near as possible to those at which the wings are expected t o be used. A number of investigations of the characteristics of swept wings at high Reynolds numbers have been made, but as yet there does not exist any related data from which the individual effects of the plan-form variables can be evaluated. <br>An investigation has been started in the Langley two-dimensional low-turbulence pressure tunnel to study, at relatively high Reynolds numbers, the effects of systematic variations in wing geometry on the low-speed aerodynamic characteristics of wings for high-speed airplanes. The present paper presents the results of tests of a series of nine wings having NACA 65A006 sections, covering a range of sweep angles from -45&#176; to 60&#176;, aspect ratios from 2 to 6, and taper ratios from 0.3 t o 1.0. Tests were made of the wings a one and with half-span split flaps at Reynolds numbers from 1.5 x 10 ⁶ to 12 x 10⁶. <br>One of these wings, of-aspect ratio 4 and with 45&#176; sweepback of the quarter-chord line, was tested with a hinged leading edge flap of various spans t-o determine the effect of this type of flap on longitudinal stability at the stall.