Scaling and configuration effects on helicopter rotor hub interactional aerodynamics

David Reich, Steven Willits, Sven Schmitz

Research output: Contribution to journalArticle

7 Citations (Scopus)

Abstract

A 1:17 scale model of a notional rotor hub of a large helicopter was tested in the Pennsylvania State University Applied Research Laboratory 12 in. test-section water tunnel. Objectives of the experiment were to quantify the 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 was tested, with hub-diameter-based Reynolds numbers ranging from 1.0 × 106 to 2.6 × 106 and advance ratios ranging from 0.2 to 0.6, as well as nonrotating cases. Five hub geometry configurations were tested with various combinations of components including blade stubs, spiders, scissors, the swashplate, pitch links, and beanie fairing. Measurements included the steady and unsteady hub drag and particle image velocimetry at two downstream locations. Results include time-averaged and phase-averaged analyses of the unsteady drag and wake velocity. A strong dependence of the steady and unsteady hub drag and wake on the advance ratio, Reynolds number, and configuration was observed, demonstrating the importance of adequate Reynolds number scaling for model helicopter rotor hub tests.

Original languageEnglish (US)
Pages (from-to)1692-1704
Number of pages13
JournalJournal of Aircraft
Volume54
Issue number5
DOIs
StatePublished - Sep 1 2017

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Helicopter rotors
Drag
Aerodynamics
Reynolds number
Rotors
Geometry
Research laboratories
Helicopters
Velocity measurement
Wind tunnels
Water
Experiments

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

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abstract = "A 1:17 scale model of a notional rotor hub of a large helicopter was tested in the Pennsylvania State University Applied Research Laboratory 12 in. test-section water tunnel. Objectives of the experiment were to quantify the 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 was tested, with hub-diameter-based Reynolds numbers ranging from 1.0 × 106 to 2.6 × 106 and advance ratios ranging from 0.2 to 0.6, as well as nonrotating cases. Five hub geometry configurations were tested with various combinations of components including blade stubs, spiders, scissors, the swashplate, pitch links, and beanie fairing. Measurements included the steady and unsteady hub drag and particle image velocimetry at two downstream locations. Results include time-averaged and phase-averaged analyses of the unsteady drag and wake velocity. A strong dependence of the steady and unsteady hub drag and wake on the advance ratio, Reynolds number, and configuration was observed, demonstrating the importance of adequate Reynolds number scaling for model helicopter rotor hub tests.",
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Scaling and configuration effects on helicopter rotor hub interactional aerodynamics. / Reich, David; Willits, Steven; Schmitz, Sven.

In: Journal of Aircraft, Vol. 54, No. 5, 01.09.2017, p. 1692-1704.

Research output: Contribution to journalArticle

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