Force and Moment Test on a Low Boom Configuration in Glenn's 8 x 6 Wind Tunnel (Invited)

Experimental aerodynamic data are presented for a wind tunnel model of a low-boom aircraft concept conducted in the NASA Glenn Research Center 8- by 6-foot Supersonic Wind Tunnel. This aircraft concept, originally designed for experimental investigations of off-body acoustics, was modified to characterize aerodynamic performance and stability parameters across a wide range of Mach numbers. Data has been obtained at chord Reynolds numbers of 1.2 to 3.9x10 6