NACA-RM-L52G11 REV A

Abstract

INTRODUCTION <br>A systematic research program is being carried out in the Langley high-speed 7- by 10-foot wind tunnel to determine the aerodynamic characteristics of various arrangements of the component parts of research-type airplane models, including some complete model configurations. Data are being obtained on characteristics in pitch and sideslip and during steady roll at Mach numbers from 0.40 to about 0.95. The Reynolds number range for the sting-supported models varies from 2 x 10⁶ to 3.5 x 10⁶, depending on the wing plan form and the test Mach number. <br>This paper presents results which show the effect of sweep on the aerodynamic characteristics in sideslip of wings of aspect ratio 4, taper ratio 0.6, and with an NACA 65A006 airfoil section in combination with a fuselage that was common to all configurations. The pitch characteristics of these wing-fuselage alone and for some of the related wing-fuselage configurations of this program are presented in reference 2. In order to expedite the issuance of the results, only a limited comparison of some of the more significant characteristics with available theory is presented.