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TECHNICAL PAPERS

Hot-Wire Measurements Around a Controlled Diffusion Airfoil in an Open-Jet Anechoic Wind Tunnel

[+] Author and Article Information
Stéphane Moreau

 Valeo Motors and Actuators, 78321 La Verrière, France

Douglas Neal, John Foss

 Michigan State University, East Lansing, MI 48823

J. Fluids Eng 128(4), 699-706 (Dec 06, 2005) (8 pages) doi:10.1115/1.2201644 History: Received January 10, 2005; Revised December 06, 2005

The aeroacoustic measurements in the large anechoic wind tunnel of Ecole Centrale de Lyon, which previously focused on the wall pressure distribution and the far-field acoustic pressure, are extended to velocity measurements by hot-wire probes in the nozzle jet and in the vicinity of a Controlled Diffusion airfoil. The present work focuses on the flow conditions corresponding to a Reynolds number based on the airfoil chord length Rec=1.6×105 and a geometric angle of attack αg of 8°. Midspan measurements were achieved at the exit plane of the wind tunnel nozzle upstream of the test airfoil and in a large eddy simulation domain that was embedded in the potential core around the airfoil mockup. The inlet measurements by a single hot-wire probe provided insight into the free-stream turbulence intensity upstream of the profile. The X-probe measurements on the upper and lower computational boundaries show the overall deflection of the jet potential core by the cambered airfoil. These are compared to previous Reynolds averaged Navier-Stokes predictions. The X-probe measurements in the airfoil wake provide information on the development of the airfoil boundary layer and the resulting wake after separation. The measured wake velocity defect has been compared with both numerical predictions.

Copyright © 2006 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Locations of measurement stations on the CD profile

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Figure 2

CD profile mounted in the ECL large wind tunnel

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Figure 3

RANS simulation of the CD profile mounted in the ECL large wind tunnel

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Figure 4

Measurement locations on the LES domain (speed contours at a given time)

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Figure 5

Pressure coefficient on the CD profile

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Figure 6

Wall pressure spectra Φpp near the trailing edge

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Figure 7

LES instantaneous velocity contours in the trailing edge region

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Figure 8

Experimental inlet mean and RMS velocity profiles at x∕C=−2.48

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Figure 9

Inlet velocity spectra at x∕C=−2.48

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Figure 10

Inlet velocity spectra at x∕C=−2.48 With the von Kármán and modified von Kármán fits

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Figure 11

Comparison of normalized numerical velocity (∣V⃗∣∕U∞) and normalized experimental mean velocity (∣V⃗∣∕Uref) profiles on the suction side LES boundary

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Figure 12

Comparison of normalized numerical (∣V⃗∣∕U∞) and normalized experimental mean velocity (∣V⃗∣∕Uref) profiles on the pressure side LES boundary

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Figure 13

Normalized experimental RMS velocity profiles on the LES boundaries: (a) Streamwise component (U∕Uref) and (b) Crosswise component (V∕Uewf)

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Figure 14

Normalized experimental mean velocity (∣V⃗∣∕Uref) profiles in the wake region at x∕C=0.056

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Figure 15

Comparison of normalized numerical (∣V⃗∣∕U∞) and normalized experimental mean velocity (∣V⃗∣∕Uref) profiles at x∕C=0.056

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Figure 16

Wake velocity spectra at x∕C=0.025 and (a) y∕C=−0.018, (b) y∕C=0.011, (c) y∕C=0.026, and (d) y∕C=0.057

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