A Qualitative Examination of Dynamic Stall from Flight Test Data

摘要

Three flight conditions from the UH-60A Airloads Program are examined where where dynamic stall occurs in the rotor: a sym- metric pull-up that includes non-zero angular rates and accelerations; a high -speed, diving turn that includes non-zero angu- lar rates, but nominally zero angular accelerations; and a level flight case with zero angular rates and accelerations. The two maneuver conditions result in severe pitch-link loads and represent design conditions for this military aircraft.