NACA-RM-A9C21

Abstract

INTRODUCTION <br>A coordinated program is being conducted at Ames Aeronautical Laboratory t o provide information throughout an extensive range of Mach and Reynolds numbers on a wing-fuselage combination employing a wing with the leading edge swept back 63&#176; and having an aspect ratio of 3.5. According to the theoretical considerations of reference 1, a wing of this plan form should be capable of efficient flight at supersonic Mach numbers up t o 1.5. Experimental results from tests of wings of this p k form at high Mach or Reynolds numbers are presented in references 2, 3, and 4. <br>A wing-fuselage combination having a wing of the plan form just described was investigated in one of the Ames 7- by 10-foot wind tunnels to evaluate the effectiveness of various flaps and particularly their capacity for eliminating the large changes in the longitudinal stability which have been found to occur above a lift coefficient of 0.4 (reference 4). In this connection, a drooped-nose flap and an extended-nose flap were tested in conjunction with trailing-edge flaps. Furthermore, an investigation was made to determine the optimum chordwise position of split flaps and the effectiveness of elevons of two different plan forms.