NACA-RM-A51H10 REV A

Abstract

<strong>INTRODUCTION</strong> <br>The results of tests of an aspect ratio 4 triangular wing (reference 1) have shown the wing to be suitable for use at supersonic speeds. In order to determine the aerodynamic charact8ristics of a similar wing at large scale and low Speed, an investigation has been conducted in the Ames 40-by 80-foot wind tunnel. <br>The results of reference 1 with regard to aerodynamic-center shift and of reference 2 with regard to damping in pitch indicate that prime consideration should be placed on the use of the wing in an airplane configuration with a horizontal tail. Therefore tests were conducted to determine the low-speed longitudinal characteristics of an airplane configuration with the aspect ratio 4 triangular wing and a horizontal tail. The results of tests reported in reference 3 shoed that the vertical position of a horizontal tail had a marked effect on the longitudinal stability of a model with an aspect ratio 2 wing; hence the vertical position of the tail was varied in the present case. In additional, the effect of a variation of tail span on the longitudinal stability was investigated.