NACA-RM-A9B17

Abstract

INTRODUCTION <br>Although low-aspect-ratio wings of triangular plan form are primarily intended for use at supersonic speeds, the designer of an airplane employing this wing design is also concerned with their low-speed characteristics, With regard to the low-speed pressure distribution on triangular wings of aspect ratio 2, reference 1 reported the results of an investigation on a triangular wing with a subsonic-type airfoil section of moderate thickness (NACA 0012). Due to the interest in wings having thinner sections, it was considered desirable to investigate the low-speed pressure distribution on a wing having the same plan form and aspect ratio but a supersonic-type airfoil section. <br>In addition, an appropriate supersonic-type body was added to the wing to determine the effect of a body on the loading of a triangular plan-form wing of low aspect ratio. Finally, the mock-up of a triangular-wing airplane of approximately the same aspect ratio, but having a thin low-drag subsonic-type airfoil section (NACA 65-006.5), was made available to the NACA for investigation. <br>The results of the pressure-distribution investigation on these large-scale models have been summarized in this report in order to make the much needed data available to designers of aircraft with wings of triangular plan form. This report, then, in conjunction with reference 1, makes available a comparison of the loading on two triangular wings, one having a relatively thick subsonic-type and the other a thin supersonic-type airfoil section. In addition, the data presented in this report indicate the effect of a body on the wing load distribution was well as providing a qualitative comparison of the loadings on two wing-body combinations, one having a thin subsonic-type and the other a thin supersonic-type airfoil section.