Skip to main content
Log in

Comparison of three-dimensional density distribution of numerical and experimental analysis for twin jets

  • Regular Paper
  • Published:
Journal of Visualization Aims and scope Submit manuscript

Abstract

Three-dimensional density fields of the twin jets were numerically and experimentally investigated. The present study focused on the comparison of the density distribution for the twin jets. The results obtained by the computational fluid dynamics (CFD) and three-dimensional background-oriented schlieren (3D-BOS) indicate that the periodic density fluctuation appears in the potential core each nozzle, and the flow structure of the twin jets is quite similar. The distribution of the normalized density value at the nozzle centerline agrees well with CFD and 3D-BOS. The density value of the shear layer between the nozzles increases as the interaction of the twin jets occurs. The trend of increasing and decreasing the interference between the nozzles was almost the same as each other. On the other hand, the position where the interaction of the twin jets starts and the growth rate of interaction were different. This is probably due to the effect of the laminar-to-turbulent transition occurred in the results of CFD. This result indicates that the laminar-to-turbulent transition can be estimated from the velocity fields obtained by CFD and particle image velocimetry (PIV).

Graphic Abstract

This is a preview of subscription content, log in via an institution to check access.

Access this article

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5
Fig. 6
Fig. 7
Fig. 8
Fig. 9
Fig. 10
Fig. 11
Fig. 12
Fig. 13
Fig. 14
Fig. 15

Similar content being viewed by others

References

  • Abe Y, Haga T, Nonomura T, Fujii K (2015) On the freestream preservation of high-order conservative flux-reconstruction schemes. J Comput Phys 281:28–54

    Article  MathSciNet  Google Scholar 

  • Abe Y, Morinaka I, Haga T, Nonomura T, Shibata H, Miyaji K (2018) Stable, non-dissipative, and conservative flux-reconstruction schemes in split forms. J Comput Phys 353:193–227

    Article  MathSciNet  Google Scholar 

  • Amiet R (1978) Refraction of sound by a shear layer. J Sound Vib 58(4):467–482

    Article  Google Scholar 

  • Bauknecht A, Ewers B, Wolf C, Leopold F, Yin J, Raffel M (2015) Three-dimensional reconstruction of helicopter blade-tip vortices using a multi-camera bos system. Exp Fluids 56(1):1–13

    Article  Google Scholar 

  • Borchers I, Goethert B (1977) An experimental study of the noise radiation of interfering free jets. In: 4th aeroacoustics conference, p 1285

  • Bozak R, Henderson B (2011) Aeroacoustic experiments with twin jets. In: 17th AIAA/CEAS aeroacoustics conference (32nd AIAA aeroacoustics conference), p 2790

  • Freund JB (1997) Proposed inflow/outflow boundary condition for direct computation of aerodynamic sound. AIAA J 35(4):740–742

    Article  Google Scholar 

  • Goldhahn E, Seume J (2007) The background oriented schlieren technique: sensitivity, accuracy, resolution and application to a three-dimensional density field. Exp Fluids 43(2–3):241–249

    Article  Google Scholar 

  • Greatrex F, Brown D (1958) Progress in jet engine noise reduction. In: The first international council of the aeronautical sciences, pp 364–392

  • Haga T, Kawai S (2019) On a robust and accurate localized artificial diffusivity scheme for the high-order flux-reconstruction method. J Comput Phys 376:534–563

    Article  MathSciNet  Google Scholar 

  • Hansen PC (1999) The l-curve and its use in the numerical treatment of inverse problems

  • Hartmann U, Adamczuk R, Seume J (2015) Tomographic background oriented schlieren applications for turbomachinery. In: 53rd AIAA aerospace sciences meeting, p 1690

  • Hirose Y, Ishikawa K, Ishimoto Y, Nagashima T, Ota M, Udagawa S, Inage T, Kiritani H, Fujita K, Fujita K et al (2019) The quantitative density measurement of unsteady flow around the projectile. J Flow Control Meas Visual 7(02):111

    Article  Google Scholar 

  • Huynh HT (2007) A flux reconstruction approach to high-order schemes including discontinuous Galerkin methods. In: 18th AIAA computational fluid dynamics conference, p 4079

  • Jarrin N, Benhamadouche S, Laurence D, Prosser R (2006) A synthetic-eddy-method for generating inflow conditions for large-eddy simulations. Int J Heat Fluid Flow 27(4):585–593

    Article  Google Scholar 

  • Kantola R (1981) Acoustic properties of heated twin jets. J Sound Vib 79(1):79–106

    Article  Google Scholar 

  • Knast T, Bell G, Wong M, Leb CM, Soria J, Honnery DR, Edgington-Mitchell D (2018) Coupling modes of an underexpanded twin axisymmetric jet. AIAA J 56(9):3524–3535

    Article  Google Scholar 

  • Nicolas F, Todoroff V, Plyer A, Le Besnerais G, Donjat D, Micheli F, Champagnat F, Cornic P, Le Sant Y (2016) A direct approach for instantaneous 3d density field reconstruction from background-oriented schlieren (bos) measurements. Exp Fluids 57(1):13

    Article  Google Scholar 

  • Nonomura T, Nakano H, Ozawa Y, Terakado D, Yamamoto M, Fujii K, Oyama A (2019) Large eddy simulation of acoustic waves generated from a hot supersonic jet. Shock Waves 29:1133–1154

    Article  Google Scholar 

  • Nonomura T, Abe Y, Ozawa Y, Fujii K (2021) Computational study on aeroacoustic fields of a transitional supersonic jet. J Am Soc Acoust 149:4484–4502

    Article  Google Scholar 

  • Ota M, Hamada K, Kato H, Maeno K (2011) Computed-tomographic density measurement of supersonic flow field by colored-grid background oriented schlieren (cgbos) technique. Meas Sci Technol 22(10):104011

    Article  Google Scholar 

  • Ota M, Kurihara K, Aki K, Miwa Y, Inage T, Maeno K (2015) Quantitative density measurement of the lateral jet/cross-flow interaction field by colored-grid background oriented schlieren (cgbos) technique. J Visual 18(3):543–552

    Article  Google Scholar 

  • Ozawa Y (2020) Aeroacoustic fields of multiple ideally expanded supersonioc jets of mach number of 2.0. Ph. D. Dissertation, Tohoku University, Japan

  • Ozawa Y, Ibuki T, Nonomura T, Suzuki K, Komuro A, Ando A, Asai K (2020a) Single-pixel resolution velocity/convection velocity field of a supersonic jet measured by particle/schlieren image velocimetry. Exp Fluids 61(6):129

    Article  Google Scholar 

  • Ozawa Y, Nonomura T, Oyama A, Asai K (2020b) Effect of the Reynolds number on the aeroacoustic fields of a transitional supersonic jet. Phys Fluids 32(4):046108

    Article  Google Scholar 

  • Ozawa Y, Saito Y, Nonomura T, Asai K (2021) Aeroacoustic fields of the supersonic twin jets at the ideally expanded condition. to appear in Transactions of the Japan Society for Aeronautical and Space Sciences

  • Raman G (1999) Supersonic jet screech: half-century from powell to the present. J Sound Vib 225(3):543–571

    Article  Google Scholar 

  • Raman G, Taghavi R (1998) Coupling of twin rectangular supersonic jets. J Fluid Mech 354:123–146

    Article  MathSciNet  Google Scholar 

  • Sabareesh VB, Srinivasan K, Sundararajan T (2012) Noise characteristics of twin-square slot jets. Int J Aeroacoust 11(5–6):629–650

    Article  Google Scholar 

  • Seiner JM, Yu JC (1984) Acoustic near-field properties associated with broadband shock noise. AIAA J 22(9):1207–1215

    Article  Google Scholar 

  • Seiner JM, Manning JC, Ponton MK (1988) Dynamic pressure loads associated with twin supersonic plume resonance. AIAA J 26(8):954–960

    Article  Google Scholar 

  • Tam CK (1995) Supersonic jet noise. Ann Rev Fluid Mech 27(1):17–43

    Article  Google Scholar 

  • Umeda Y, Ishii R (1997) Oscillation modes of supersonic multijets. J Acoust Soc Am 101(6):3353–3360

    Article  Google Scholar 

  • Umeda Y, Ishii R (2001) Oscillation modes of supersonic multijets exhausting from very adjacent multiple nozzles. J Acoust Soc Am 110(4):1873–1877

    Article  Google Scholar 

  • Venkatakrishnan L, Wiley A, Kumar R, Alvi F (2011) Density field measurements of a supersonic impinging jet with microjet control. AIAA J 49(2):432–438

    Article  Google Scholar 

Download references

Acknowledgements

This work was supported by JSPS KAKENHI Grant Number JP20H00278, JP19KK0361, JP17H03473 and JP21J20744. We used JAXA Supercomputer System generation 2 (JSS2) for the CFD analysis.

Author information

Authors and Affiliations

Authors

Corresponding author

Correspondence to Chungil Lee.

Additional information

Publisher's Note

Springer Nature remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.

Appendix A: Uncertainty analysis of 3D-BOS

Appendix A: Uncertainty analysis of 3D-BOS

The 3D-BOS uncertainty analysis was investigated by verifying the repeatability of the 3D-BOS method using the matrix formulation. Ten three-dimensional density fields of the twin jets can be obtained because we captured the ten background images at each projection angle. Here, three-dimensional density fields of the twin jets for each case are a well-averaged density fields because the shutter speed is sufficiently long averaging time. Figure 16 shows the profile results of the averaged density value and the standard deviation of the measurement for the xy and yz slices. The block line of this figure presents the averaged density value, and the gray region corresponds to the standard deviation. These results show that the standard deviation of the symmetric line and the yz slice at \(s/D =\) 12 is larger than those of the nozzle centerline and the yz slice at \(s/D =\) 4.

These standard deviations are caused by the deviations in the displacements of the background. Figure 17 shows the averaged displacement of vertical direction (x axis) and horizontal direction (y axis) in the projection angle 90\(^\circ\). Figure 18 shows the profile results of the averaged displacement value and the standard deviation in each displacement direction of the nozzle centerline (\(y/D =\) 0.5\(\times\)s) and symmetric line (\(y/D =\) 0). These results indicate that the standard deviation in each displacement direction is large, and in particular, the standard deviation in symmetric line is the largest. This is because the displacements vary in each case in the region where interaction of the twin jets occurs. These results illustrate that the larger standard deviation is observed in the area where interference between the nozzles occurs. Although the standard deviation is larger because of the interaction of the twin jets, the value is still sufficiently small in the area. Therefore, the 3D-BOS method using the matrix formulation is considered to be reliable.

Fig. 16
figure 16

Standard deviation of the xy and yz slices

Fig. 17
figure 17

Mean displacement in the projection angle 90\(^\circ\)

Fig. 18
figure 18

Standard deviation of displacement

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Lee, C., Ozawa, Y., Haga, T. et al. Comparison of three-dimensional density distribution of numerical and experimental analysis for twin jets. J Vis 24, 1173–1188 (2021). https://doi.org/10.1007/s12650-021-00765-z

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s12650-021-00765-z

Keywords

Navigation