Slowed rotor wind tunnel testing of an instrumented rotor at high advance ratio

dc.contributor.author Berry, B.
dc.contributor.author Chopra, I.
dc.date.accessioned 2016-12-16T15:14:37Z
dc.date.available 2016-12-16T15:14:37Z
dc.date.issued 2014
dc.description.abstract Compound helicopter designs utilize a slowed main rotor, which reduces RPM as flight speed increases to maintain sub-critical tip Mach numbers. These concepts are therefore expected to operate at high advance ratios (1–2.5 or higher). There is a need for experimental data sets in this flight regime to validate and devel-op predictive tools. Systematic testing in the Glenn L. Martin Wind Tunnel (University of Maryland) was con-ducted on an instrumented Mach-scale articulated rotor (1.7 m diameter) up to an advance ratio of 1.61. The following measurements were taken: steady and dynamic 6-component hub loads (fixed-frame), shaft torque (rotating frame), root flapping angles, pitch link loads, blade torsion and flap bending moments at 5 spanwise stations, and 16 chordwise blade pressures at 30% radius spanwise location. The selected results detailed in this paper revealed insights into high advance ratio, reverse flow phenomenon such as reverse chord dy-namic stall and the resulting impact on loads. The combination of rotor advance ratios beyond 1.0, large col-lective pitch sweeps, and blade surface pressure measurements makes this data set unique.
dc.identifier.other 20-C-paper
dc.identifier.uri http://hdl.handle.net/20.500.11881/3463
dc.language.iso en
dc.title Slowed rotor wind tunnel testing of an instrumented rotor at high advance ratio
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