Effects of the air breathing engine plumes on SSV orbiter subsonic wing pressure distributions (OA57A)

Experimental aerodynamic pressure investigations were conducted on a 0.0405 scale representation of the -89 space shuttle orbiter ferry configuration in the Rockwell International 7.75 x 11.00 foot Low Speed Wind Tunnel. The primary test objective was to investigate the orbiter wing pressure distribution resulting from five under-wing engine nacelle plumes. Two five engine nacelle configurations were tested at 3 ground plane heights with pressure bug measurements being made on the left upper and lower wing panel. In addition, base and balance cavity pressure measurements were made, with elevon normal and hinge moment measurements on the right panel.