NACA-RM-A53C20

Abstract

INTRODUCTION <br>Research is in progress at the various NACA facilities to determine the aerodynamic characteristics of flap-type, trailing-edge elevons on low-aspect-ratio wings at both subsonic and supersonic speeds. The effects of elevon plan form and trailing-edge profile on the aerodynamic characteristics of elevons on a thin triangular wing of aspect ratio 2 have been determined at high subsonic and low supersonic speeds and have been reported in references. <br>As a part of this research, there are reported herein results of tests conducted in the Ames 12-foot pressure wind tunnel at Mach numbers up to 0.95 to determine the aerodynamic characteristics of constant-percent-chord, flap-type trailing-edge elevons on a pointed wing having an aspect ratio of 2. The effectiveness of inset tabs in reducing the elevon hinge monent is also presented. The wing leading edge was swept back 56.3&#176; and the trailing edge was swept forward 26.6&#176;