NACA-RM-L50K14

Abstract

INTRODUCTION <br>An investigation has been conducted in the Langley 4- by h-foot supersonic tunnel to determine the aerodynamic characteristics of a relatively large size model of a swept-wing supersonic aircraft configuration. Tests have been conducted on both a force and pressure model of identical configuration at Mach numbers of 1.40 and 1.59 at a Reynolds number of approximately 0.6 x 10⁶ based on wing mean aerodynamic chord. References 1 to 8 present the results of various phases of this investigation. Tests of a small-scale model of the same configuration in the Langley 9-inch.supersonic tunnel are reported in reference 9. An investigation of a rocket-powered model of the same configuration is reported in reference 10. <br>The present paper deals with the longitudinal- and lateral-force characteristics of the complete aircraft configuration and of various combinations of its components. The data have been analyzed insofar as possible to show the aerodynamic characteristics of each component and the interferences between components. Also included for comparison are some of the integrated pressure results for the wing from reference 3. <br>The force-model configurations tested were built up by adding to the basic sting-mounted body of revolution in various combinations the canopies, wing, vertical tail, and horizontal tail. The effects of wing-tip skids and stall-control. vanes mounted on the wing were also determined.