NACA-RM-A54D19

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 data for high angles of attack, a program has been initiated to measure pressure distribution 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>The present report presents pressure-distribution data to high angles of attack for several wings at two supersonic Mach numbers. The following data are presented: (1) tabulated pressure coefficients, (2) span-load-distribution curves for each angle of attack, (3) curves of normal force as a function of angle of attack, and (4) curves of center-of-pressure position as a function of angle of attack.