A series of aerodynamic performance and acoustic measurements has been made on a high-lift propeller intended for utilization on a distributed electric propulsion (DEP) aircraft. Tests were performed in the NASA Langley Low Speed Aeroacoustic Wind Tunnel (LSAWT), which has recently undergone a capability enhancement for the testing of small propellers/rotors and small unmanned aircraft system (UAS) platforms. The objectives of this testing campaign are two-fold: first to demonstrate the facility capabilities for performing small propeller aeroacoustic testing, and second to compare experimental measurements with computational fluid dynamic (CFD) predictions and CFD-based acoustic predictions of the tested propeller configurations for tool development and validation purposes.
Aerodynamic Performance and Acoustic Measurements of a High-Lift Propeller in an Isolated Configuration
2018
16 pages
Report
No indication
English
Acoustics , Aerodynamic characteristics , Acoustic measurement , Propellers , Lift augmentation , Electrified aircraft propulsion , Propulsion system configurations , Aeroacoustics , Computational fluid dynamics , Small unmanned aircraft systems , Pilotless aircraft , Low speed wind tunnels , Rotors
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