SUBSONIC WIND-TUNNEL INVESTIGATION OF THE AERODYNAMIC EFFECTS OF PIVOTING A LOW-ASPECT-RATIO WING TO LARGE YAW ANGLES WITH RESPECT TO THE FUSELAGE TO INCREASE LIFT-DRAG RATIO

摘要

An investigation has been made with a fuselage in combination with low-aspect-ratio wings of various plan forms to determine the effects of pivoting the wing as a unit to extreme angles in the yaw direction with respect to the fuselage to increase its aspect ratio. An arrangement of this type has been suggested as a possible means of reducing the high sinking speeds and improving the landing characteristics of airplanes having wings of very low aspect ratio for flight at hypersonic speeds. Three wing plan forms were tested - a delta, a diamond, and a rectangle with the wing pivoted at angles between the wing and fuselage center lines from 0° to 109°• The investigation was made in the Langley high-speed 7- by 10-foot tunnel at a Mach number of about 0.4 and a Reynolds number (based on fuselage length) of about 3 X 10. Lift, drag, pitching-moment, and rolling-moment data were obtained through an angle-of-attack range of -4° to about 24º. The effects of varying the wing pivot-point location for the delta-wing model were determined, and the delta-wing model was tested with the forward portion of the wing deflected about its center line for roll control and also with a horizontal tail added to the rear of the fuselage.