This model test is part of an experimental and computational effort aimed at determining the influence of chine-shaped fuselage cross sections on the interactions between forebody and wing vortices. During the tests surface pressures, force and moment measurements, as well as limited off-body flow visualization were obtained. The data were taken in the Langley 7 x 10 foot High Speed Tunnel (shown here) and the Langley 8 foot Transonic Pressure Tunnel.
