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Research Papers

A Modified Dynamic Stall Model for Low Mach Numbers

[+] Author and Article Information
W. Sheng

 University of Glasgow, Glasgow G12 8QQ, UKwsheng@aero.gla.ac.uk

R. A. Galbraith

 University of Glasgow, Glasgow G12 8QQ, UKr.a.m.galbraith@aero.gla.ac.uk

F. N. Coton

 University of Glasgow, Glasgow G12 8QQ, UKf.coton@aero.gla.ac.uk

J. Sol. Energy Eng 130(3), 031013 (Jul 03, 2008) (10 pages) doi:10.1115/1.2931509 History: Received February 28, 2007; Revised October 05, 2007; Published July 03, 2008

The Leishman–Beddoes dynamic stall model is a popular model that has been widely applied in both helicopter and wind turbine aerodynamics. This model has been specially refined and tuned for helicopter applications, where the Mach number is usually above 0.3. However, experimental results and analyses at the University of Glasgow have suggested that the original Leishman–Beddoes model reconstructs the unsteady airloads at low Mach numbers less well than at higher Mach numbers. This is particularly so for stall onset and the return from the fully stalled state. In this paper, a modified dynamic stall model that adapts the Leishman–Beddoes dynamic stall model for lower Mach numbers is proposed. The main modifications include a new stall-onset indication, a new return modeling from stalled state, a revised chordwise force, and dynamic vortex modeling. The comparisons to the Glasgow University dynamic stall database showed that the modified model is capable of giving improved reconstructions of unsteady aerofoil data in low Mach numbers.

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Copyright © 2008 by American Society of Mechanical Engineers
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Figures

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Figure 1

Normal force including DS for NACA 0012 aerofoil at a low Mach number of 0.12, and reduced frequency of 0.124. Legend: 1—Beddoes’ DS model and 2—Leishman’s reattachment modification (measured data from the Glasgow dynamic database)

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Figure 2

Force reconstructions via Eqs. 5,5,5 for NACA 0012 static test

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Figure 3

Separation location, f, in static state, and its delayed value, f′, for an oscillatory case

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Figure 4

A schematic graph for the new stall-onset criterion of Sheng

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Figure 5

αmin versus the absolute values of reduced pitch rate, ∣r∣

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Figure 6

Profiles of NACA 0012 and S809 aerofoils

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Figure 7

Force reconstructions for a NACA0012 ramp-up test (r=0.0145). (a) Normal force, (b) Pitching moment, (c) Chordwise force, and (d) Drag.

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Figure 8

Force reconstructions for an S809 ramp-up test (r=0.0169). (a) Normal force, (b) Pitching moment, (c) Chordwise force, and (d) Drag.

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Figure 9

Force reconstructions for a NACA 0012 oscillatory test (α=15deg+10degsinωt,κ=0.124). (a) Normal force, (b) Pitching moment, (c) Chordwise force, and (d) Drag.

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Figure 10

Force reconstructions for an S809 oscillatory test (α=15deg+10degsinωt,κ=0.074). (a) Normal force, (b) Pitching moment, (c) Chordwise force, and (d) Drag.

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Figure 11

Normal force reconstructions for an S809 oscillatory test (κ=0.05). (a) α=10 deg +4 deg sinωt and (b) α=10 deg +6 deg sinωt.

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Figure 12

Normal force reconstructions for an S809 oscillatory test (κ=0.10). (a) α=10 deg +4 deg sinωt and (b) α=10 deg +6 deg sinωt.

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