TY - JOUR
T1 - Effects of reynolds number and advance ratio on the drag of a model helicopter rotor hub
AU - Reich, David
AU - Willits, Steven
AU - Schmitz, Sven
N1 - Publisher Copyright:
© 2014 by the American Helicopter Society International, Inc.
PY - 2015
Y1 - 2015
N2 - A 1:17 scale model of a notional rotor hub of a large helicopter was tested in the Pennsylvania State University (PSU) Applied Research Laboratory (ARL) 12-inch test section water tunnel. Objectives of the experiment were to quantify effects of Reynolds number, advance ratio, and hub geometry configuration on the drag and shed wake of the rotor hub. A range of flow conditions were tested, with hub diameter-based Reynolds numbers ranging from 1.06 × 105 to 2.62 × 106 and advance ratios ranging from 0.2 to 0.4, as well as non-rotating cases. Three hub geometry configurations were tested with various combinations of components including fairing, blade stubs, spiders, scissors, swashplate, and pitch links. Primary measurements were steady and unsteady hub drag and Particle Image Velocimetry at two downstream locations. Results include time-averaged, phase-averaged, spectral analysis of the unsteady drag, and wake velocity. A strong dependence of steady and unsteady drag on Reynolds number and advance ratio was noted, eluding to the importance of adequate Reynolds scaling for model helicopter rotor hub tests.
AB - A 1:17 scale model of a notional rotor hub of a large helicopter was tested in the Pennsylvania State University (PSU) Applied Research Laboratory (ARL) 12-inch test section water tunnel. Objectives of the experiment were to quantify effects of Reynolds number, advance ratio, and hub geometry configuration on the drag and shed wake of the rotor hub. A range of flow conditions were tested, with hub diameter-based Reynolds numbers ranging from 1.06 × 105 to 2.62 × 106 and advance ratios ranging from 0.2 to 0.4, as well as non-rotating cases. Three hub geometry configurations were tested with various combinations of components including fairing, blade stubs, spiders, scissors, swashplate, and pitch links. Primary measurements were steady and unsteady hub drag and Particle Image Velocimetry at two downstream locations. Results include time-averaged, phase-averaged, spectral analysis of the unsteady drag, and wake velocity. A strong dependence of steady and unsteady drag on Reynolds number and advance ratio was noted, eluding to the importance of adequate Reynolds scaling for model helicopter rotor hub tests.
UR - https://www.scopus.com/pages/publications/84937877510
UR - https://www.scopus.com/inward/citedby.url?scp=84937877510&partnerID=8YFLogxK
M3 - Article
AN - SCOPUS:84937877510
SN - 1552-2938
VL - 1
SP - 443
EP - 463
JO - Annual Forum Proceedings - AHS International
JF - Annual Forum Proceedings - AHS International
IS - January
ER -