An investigation has been conducted in the NASA Langley Research Cente
r's 14 by 22 ft Subsonic Tunnel to further the development of semispan
testing capabilities, A twin-engine, energy efficient transport model
with a four-element wing in a takeoff configuration was used for this
investigation. Initially, a full-span configuration was tested, and f
orce and moment data and wing and fuselage surface pressure data were
obtained as a baseline data set, The semispan configurations were then
mounted on the wind-tunnel door, and the effects of fuselage standoff
height and shape were investigated. Results indicate that the semispa
n configuration was sensitive to variations in standoff height, and th
at a standoff height equivalent to 30% of the fuselage radius resulted
in better correlation with full-span data than no standoff or the lar
ger standoff configurations investigated, Undercut standoff leading ed
ges improved the correlation of semispan data with full span data in t
he region of maximum lift coefficient.