EXPERIMENTAL INVESTIGATION OF TRANSITION OF A MODEL HELICOPTER ROTOR FROM HOVERING TO VERTICAL AUTOROTATION

摘要

An experimental investigation has been carried out to study the variation of average induced flow around a model helicopter during transition from a hovering condition to steady authoritative vertical descent. Test data were obtained from simulated power failures under many different conditions. Results are summarized for variations in disk loading, blade angles, and rate of pitch change. Calculations were made of ''effective induced velocity" for the various conditions. Sample comparisons of calculated and experimental performance were made.