Near wakes of advanced turbopropellersThe flow in the wake of a model single rotation Prop-Fan rotor operating in a wind tunnel was traversed with a hot-wire anemometer system designed to determine the 3 periodic velocity components. Special data acquisition and data reduction methods were required to deal with the high data frequency, narrow wakes, and large fluctuating air angles in the tip vortex region. The model tip helical Mach number was 1.17, simulating the cruise condition. Although the flow field is complex, flow features such as viscous velocity defects, vortex sheets, tip vortices, and propagating acoustic pulses are clearly identified with the aid of a simple analytical wake theory.
Document ID
19890046364
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hanson, D. B. (United Technologies Corp. Hamilton Standard Div., Windsor Locks, CT, United States)
Patrick, W. P. (United Technologies Research Center East Hartford, CT, United States)