NACA-RM-A54J12

Abstract

INTRODUCTION <br>Since wings and controls for supersonic interceptor aircraft maneuvering at high altitudes are required to operate over a wide range of angles of attack, information is required on wing-load distribution at large as well as small angles of attack. Unfortunately, available theory on the aerodynamic behavior of wing and wing-body configurations at supersonic speeds is restricted to cases, where the angle of attack is small. Detailed pressure-distribution data on wing-body components available in the literature (e.g., refs. 1 to 3) are also generally limited to small angles of attack. Little data are available for high angles of attack at supersonic speeds, particularly for wing-body models with variable-incidence wings. In an effort to provide the needed information, a program has been initiated to measure pressure distributions through a wide range of angles of attack, both on wing-body combinations and on the components (wing and body). It is hoped that the data obtained will not only provide needed design information, but will also point the way for development of theories applicable over a wide range of angles of attack. <br>Five low-aspect-ratio wings of triangular and rectangular plan form were chosen for the initial experimental investigation. Pressure distributions on these wings through a wide range of angles of attack at Mach numbers of 1.45 and 1.97 were presented in reference 4. The present report presents similar data for Mach numbers of 2.46 and 3.36. Specifically, the data are presented in the form of: (1) tabulated pressure coefficients, (2) span-load-distribution (3) curves of normal force as a function angle of attack, and (4) curves of center-of-pressure position as a function of angle of attack.