Hydrodynamic flowfield visualization studies of a Mach 6 waverider

Abstract

Flowfield visualization studies of a conical flow derived waverider were conducted in the Naval Postgraduate School water tunnel facility, as part of an ongoing study by the Naval Postgraduate School and the NASA Ames Research Center. The model, with an 8 inch root chord, 7.5 inch span and an aspect ratio of 1.41, was designed and constructed with an integrated forebody engine inlet ramp system and cowling for a hydrocarbon scramjet type propulsion system. Still photographs and video frames were taken for pitch angles between 00 and 200 and yaw angles between 00 and 100. The waverider flowfield was similar to that associated with sharp leading edge delta wings with the primary vortex separating at the leading edge and rolling up over the upper surface. However, a comparison of waverider with delta wing data suggests that vortex core breakdown occurred at much lower angles of attack on the blunt nosed (planform) waverider Waverider, Flow visualization by dye injection, Water tunnel studies, Vortex development and bursting, Effect of static angle of attack and sideslip