WITH AND WITHOUT NACELLES AT THE WING TIPS

Rocket-propelled models were flight-tested at transonic speeds to compare the aero-lift drags of hS0 sweptback wings having-aspect ratios of 3.55 and 6.0 with and without solid nacelles at the wing tips. The aspect-ratio-3-55 wing was derived by removing 35.5 percent of the semi-span from the outboard part of the aspect-ratio-6.0 wing. The fuselage and nacelle fineness ratios were 10.0 and 9.66, respectively. The wings had the NACA 6 5 ~ 0 0 9 airfoil section in the free-stream direction. The wing drag coefficient was lowered at high subsonic and super-sonic speeds when the aspect ratio w a s reduced from 6.0 to 3.55. Near a Mach number of 1.0, decreasing the aspect ratio increased the wing drag coefficient. The wing-tip nacelle locations on both the high- and low-aspect-ratio wings were favorable from a drag standpoint; however, less favorable nacelle-plus-interference drag was obtained at the wing tip by reducing the span of the high-aspect-ratio wing. The force-break Mach number of the configuration w a s reduced from 0.96 to 0.93 by removing 35.5 percent of the semispan from the aspect-ratio-6.0 wing