Finite control volume and scalability effects in velocimetry for application to aeroacoustics

Experiments in Fluids volume 62, Article number: 33 (2021) Cite this article

Abstract

The ability to scale the field of view for velocimetry methods is particularly attractive for aeroacoustics studies, where turbulence contributions in long-lived, low wavenumber structures account for the most important sources of radiated noise. Thanks to its core operating principles, Doppler global velocimetry (DGV) offers interesting opportunities for large-scale flow measurements. As is well known, a larger field-of-view (FOV) in the measurement will change the spatial resolution, meaning that each measurement is integrated across a larger control volume. This finite size will affect the velocity and turbulence measurements, as well as the observable wavenumbers in the measurement. The present study confirms the viability of DGV for studying low wavenumbers while examining the influence on higher wavenumbers of the less coherent turbulent structures also present in high-speed flows. In the flows examined by the current work, mean velocity bias error due to integration over the measurement region was shown to be small, less than 0.005%, for control volume heights up to 4 mm. Although significant energy attenuation occurs for high wavenumbers, the low wavenumber turbulent structures which dominate far-field noise are found to be unaffected by the size of the control volume required for large measurement of both laboratory- and full-scale supersonic jet flows. The results indicate a large-scale velocimetry system such as DGV can be a valuable tool for researchers to study aeroacoustics in high-speed flows.

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References

  1. Beutner T, Elliott G, Mosedale A, Carter C (1998) Doppler global velocimetry applications in large scale facilities. 20th aiaa advanced measurement and ground testing technology conference. In: 20th AIAA Advanced Measurement and Ground Testing Technology Conference, p 20, https://doi.org/10.2514/6.1998-2608

  2. Crighton D (1975) Basic principles of aerodynamic noise generation. Prog Aerosp Sci 16(1):31–96. https://doi.org/10.1016/0376-0421(75)90010-X

    Article  Google Scholar 

  3. Daniel KA, Mayo DE Jr, Lowe KT, Ng WF (2019) Use of thermal nonuniformity to reduce supersonic jet noise. AIAAJ Express Article 57(10):4467–4475. https://doi.org/10.2514/1.J058531

    Article  Google Scholar 

  4. Durst F, Jovanović J, Sender J (1995) Lda measurements in the near-wall region of a turbulent pipe flow. J Fluid Mech 295:305–335. https://doi.org/10.1017/S0022112095001984

    Article  Google Scholar 

  5. Ecker T, Brooks D, Lowe KT, Ng WF (2014) Development and application of a point doppler velocimeter featuring two-beam multiplexing for time-resolved measurements of high-speed flow. Exp Fluids 55:1819–1833. https://doi.org/10.1007/s00348-014-1819-0

    Article  Google Scholar 

  6. Ecker T, Lowe KT, Ng W (2016) Scale-up of the time-resolved doppler global velocimetry technique. In: 54th AIAA Aerospace Sciences Meeting, p 0029, https://doi.org/10.2514/6.2016-0029

  7. Fischer A, Büttner L, Czarske J, Egger M, Grosche G, Müller H (2007) Investigation of time-resolved single detector doppler global velocimetry using sinusoidal laser frequency modulation. Meas Sci Technol 18(8):2529–2545. https://doi.org/10.1088/0957-0233/18/8/029

    Article  Google Scholar 

  8. Fischer M, Jovanović J, Durst F (2000) Near-wall behaviour of statistical properties in turbulent flows. Int J Heat Fluid Fl 21(5):471–479. https://doi.org/10.1016/S0142-727X(00)00034-5

    Article  Google Scholar 

  9. Gamba M, Clemens NT (2011) Requirements, capabilities, and accuracies of time-resolved piv in turbulent reacting flows. In: 49th AIAA Aerospace Sciences Meeting, p 32, https://doi.org/10.2514/6.2011-362

  10. Gürtler J, Haufe D, Schulz A, Bake F, Enghardt L, Czarske J, Fischer A (2016) High-speed camera-based measurement system for aeroacoustic investigations. J Sens Sens Syst 5:125–136. https://doi.org/10.5194/jsss-5-125-2016

    Article  Google Scholar 

  11. Jenkins L, Yao C, Bartram S, Harris J, Allan B, Wong O, Mace W (2009) Development of a large field-of-view piv system for rotorcraft testing in the 14- x 22-foot subsonic tunnel. In: American Helicopter Society 65th Annual Forum, p 22

  12. Jordan P, Colonius T (2013) Wave packets and turbulent jet noise. Annu Rev Fluid Mech 45:173–195. https://doi.org/10.1146/annurev-fluid-011212-140756

    MathSciNet  Article  MATH  Google Scholar 

  13. Koschatzky V, Moore P, Westerweel J, Scarano F, BJ B (2011) High speed piv applied to aerodynamic noise investigation. Exp Fluids 50:863–876. https://doi.org/10.1007/s00348-010-0935-8

    Article  Google Scholar 

  14. Liu J, Corrigan AT, Kailasanath K, Taylor BD (2016) Impact of the specific heat ratio on noise generation in a high-temperature supersonic jet. In: 54th AIAA Aerospace Sciences Meeting, p 26, https://doi.org/10.2514/6.2016-2125

  15. Mayo DE Jr, Daniel KA, Lowe KT, Ng WF (2019) Mean flow and turbulence of a heated supersonic jet with temperature non-uniformity. AIAAJ 57(8):3493–3500. https://doi.org/10.2514/1.J058163

    Article  Google Scholar 

  16. Meyers JF, Komine H (1991) Doppler global velocimetry a new way to look at velocity. In: ASME Fourth International Conference on Laser Anemometry, p 21

  17. Meyers JF, Lee JW, Fletcher MT, South BW (2004) Hardening doppler global velocimetry systems for large wind tunnel applications. In: NASA Technical Report 20040090487, p 30

  18. Moore P, Violato D, Bryon K, Scarano F (2010) On the suitability of direct application of acoustic theory to time-resolved tomographic piv tested by dns for low mach number jet flows. In: 16th AIAA/CEAS Aeroacoustics Conference, p 13, https://doi.org/10.2514/6.2010-3960

  19. Moore P, Lorenzoni V, Scarano F (2011) Two techniques for piv-based aeroacoustic prediction and their application to a rod-airfoil experiment. Exp Fluids 50:877–885. https://doi.org/10.1007/s00348-010-0932-y

    Article  Google Scholar 

  20. Morris PJ (2009) A note on noise generation by large scale turbulent structures in subsonic and supersonic jets. Int J Aeroacoust 8(4):301–315. https://doi.org/10.1260/147547209787548921

    MathSciNet  Article  Google Scholar 

  21. Pope SB (2000) Turbulent Flows. Cambridge University Press, Cambridge

    Google Scholar 

  22. Raffel M, Mulleners K, Kindler K, Heineck J (2012) Particle image velocimetry in helicopter aerodynamics: developments, challenges, and trends. In: American Helicopter Society 68th Annual Forum, p 9

  23. Saltzman AJ, Lowe KT, Ng WF (2020) 250 khz three-component doppler global velocimetry at 32 simultaneous points: a new capability for high speed flows. Meas Sci Technol 31(9):12. https://doi.org/10.1088/1361-6501/ab8ee9

    Article  Google Scholar 

  24. Stuber M, Lowe KT, Ng WF (2019) Synthesis of convection velocity and turbulence measurements in three-stream jets. Exp Fluids 60(83):12. https://doi.org/10.1007/s00348-019-2730-5

    Article  Google Scholar 

  25. Tam CK, Viswanathan K, Ahuja KK, Panda J (2008) The sources of jet noise: experimental evidence. J Fluid Mech 615:253–292. https://doi.org/10.1017/S0022112008003704

    Article  MATH  Google Scholar 

  26. Thurow BS, Jiang N, Lempert WR, Samimy M (2005) Development of megahertz-rate planar doppler velocimetry for high-speed flows. AIAAJ 43(3):500–511. https://doi.org/10.2514/1.7749

    Article  Google Scholar 

  27. Wadcock A, Yamauchi G, Solis E, Pete A (2011) Piv measurements in the wake of a full-scale rotor in forward flight. In: 29th AIAA Applied Aerodynamics Conference, p 23, https://doi.org/10.2514/6.2011-3370

  28. Wernet MP (2007) Temporally resolved piv for space time correlations in both cold and hot jet flows. Meas Sci Technol 18(5):1387–1403. https://doi.org/10.1088/0957-0233/18/5/027

    Article  Google Scholar 

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  1. Advanced Propulsion and Power Laboratory, Virginia Tech, Blacksburg, VA, 24061, USA

    Ashley J. Saltzman, K. Todd Lowe & Wing F. Ng

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  1. Ashley J. Saltzman
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  2. K. Todd Lowe
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  3. Wing F. Ng
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Correspondence to Ashley J. Saltzman.

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Saltzman, A.J., Lowe, K.T. & Ng, W.F. Finite control volume and scalability effects in velocimetry for application to aeroacoustics. Exp Fluids 62, 33 (2021). https://doi.org/10.1007/s00348-021-03138-2

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