Expansion Side Flow Field Impact Pressure Surveys of a 75-Deg delta Wing at Mach Number 10

摘要

Impact pressure surveys were obtained in the leeward flow field of a 75-deg sharp leading-edge delta wing. Tests were conducted at a Mach number of 10.13, Reynolds number (based on model length) of 430,000, angles of attack of 15 and 19 deg, and zero sideslip angle. Abrupt pressure changes were observed in the flow field between the model surface and bow shock. Representative results are presented for alpha = 15 deg. (Author)