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Research Papers: Flows in Complex Systems

Flowfield Investigation at Propeller Thrust Reverse

[+] Author and Article Information
Eric W. M. Roosenboom

Department of Experimental Methods, Deutsches Zentrum für Luft- und Raumfahrt (DLR), Institute of Aerodynamics and Flow Technology, Bunsenstrasse 10, 37073 Göttingen, Germanyeric.roosenboom@dlr.de

Andreas Schröder

Department of Experimental Methods, Deutsches Zentrum für Luft- und Raumfahrt (DLR), Institute of Aerodynamics and Flow Technology, Bunsenstrasse 10, 37073 Göttingen, Germanyandreas.schroeder@dlr.de

J. Fluids Eng 132(6), 061101 (May 19, 2010) (8 pages) doi:10.1115/1.4001677 History: Received July 28, 2009; Revised January 28, 2010; Published May 19, 2010; Online May 19, 2010

The flow phenomena in the slipstream around an eight-bladed propeller at thrust reverse conditions are analyzed using double stereoscopic particle image velocimetry in the Airbus Low-Speed Wind Tunnel Facility in Bremen, Germany. Several planes are scanned using a traversing system, as well as measurements at several phase angles. In the present paper only properties in the propeller symmetry plane will be compared. The fluid mechanical properties for two different propeller blade pitch angle settings are investigated and compared for their ability to deliver a negative thrust. The first setting has identical blade pitch angles for all propeller blades; the second setting has alternating blade pitch angles. It is concluded that the latter setting provides better aerodynamic flow properties.

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Copyright © 2010 by American Society of Mechanical Engineers
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Figures

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Figure 1

Velocity perceived by propeller blade, and related forces at propeller thrust reverse. (Note: Not to scale and negative lift and thrust vectors are drawn in their acting directions.)

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Figure 2

Wind tunnel layout

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Figure 3

Propeller half-model in the wind tunnel

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Figure 4

Laser, optics, and traverse outside the wind tunnel test-section

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Figure 5

Detail of double stereoscopic camera setup, underneath the wind tunnel floor. Cameras 1 and 2 (stereo system 1) observe the flow downstream of the propeller; Cameras 3 and 4 (stereo system 2) observe the flow upstream of the propeller.

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Figure 6

Histogram of U-velocities showing the effect of phase-only filter; (a) phase-only filter emphasizes peak-locking (no median and Gaussian filter applied); (b) peak-locking reduced without application phase-only filter and after application of median and Gaussian filters

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Figure 7

Field of view (magnitude of velocity is displayed) during measurements, with respect to wind tunnel model. (Note that the axes are nonuniformly scaled to increase visibility, flow is from right to left.)

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Figure 8

Magnitude of velocity at the two settings (in outboard propeller symmetry plane)

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Figure 9

Comparison of averaged velocity components at the two settings (in outboard propeller symmetry plane)

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Figure 10

Differences in velocity of both settings

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Figure 11

Vorticity downstream of propeller for both settings

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Figure 12

Vorticity (top) and turbulence (bottom) generation for Setting 1 at subsequent phases in the tip region (the upper part in Fig. 1); (a) vorticity, phase angle 0 deg, (b) vorticity, phase angle 18 deg, (c) vorticity, phase angle 36 deg; (d) TKE, phase angle 0 deg, (e) TKE, phase angle 18 deg, and (f) TKE, phase angle 36 deg

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Figure 13

Vorticity (top) and turbulence (bottom) generation for Setting 2 at subsequent phases in the tip region (the upper part in Fig. 1); (a) vorticity, phase angle 0 deg, (b) vorticity, phase angle 36 deg, (c) vorticity, phase angle 72 deg; (d) TKE, phase angle 0 deg, (e) TKE, phase angle 36 deg, and (f) TKE, phase angle 72 deg

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