SpringerLink
Log in

Numerical and Experimental Analysis of Three-Dimensional Boundary-Layer Transition Induced by Isolated Cylindrical Roughness Elements

  • Original Paper
  • Published:
International Journal of Aeronautical and Space Sciences Aims and scope Submit manuscript

Abstract

Extensive research to establish an index of roughness that causes abrupt turbulent transition downstream of the roughness and affect natural laminar flow is performed. This study investigates turbulent transitions dominated by the roughness-induced crossflow instability on a swept wing and a swept flat plate. Direct numerical simulations (DNS) are performed considering the swept wing to determine the critical roughness height that induces abrupt turbulent transition. Compared to its no-roughness counterpart, the roughness increases both the pressure drag and skin-friction drag and decreases the lift owing to the onset of upstream turbulence. The wind tunnel tests are performed considering a swept flat-plate boundary-layer model. The development of turbulent regions due to the roughness is investigated. The results reveal the occurrence of a laminar-to-turbulent transition and relaminarization, along the boundary between laminar and localized turbulent regions. Moreover, the DNS results reveal the generation of traveling crossflow vortices from the localized turbulent region.

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

Access this article

Log in via an institution

Subscribe and save

Springer+ Basic
EUR 32.99 /Month
  • Get 10 units per month
  • Download Article/Chapter or Ebook
  • 1 Unit = 1 Article or 1 Chapter
  • Cancel anytime
Subscribe now

Buy Now

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

Instant access to the full article PDF.

Institutional subscriptions

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

  1. Tokugawa N, Toyoda K, Kuroda F, Ueda Y, Ishida T (2021) Natural laminar flow design for highly swept wing. In: Proceedings of the 12th Asia-Pacific international symposium on aerospace technology (APISAT 2021), P00234

  2. Holms BJ, Obara CJ, Martin GL, Domack CS (1985) Manufacturing tolerances for natural laminar flow airframe surfaces. SAE Trans 94:522–531. https://doi.org/10.4271/850863

    Article  Google Scholar 

  3. Saric WS, Reed HL, White EB (2003) Stability and transition of three-dimensional boundary layers. Annu Rev Fluid Mech 35(1):413–440. https://doi.org/10.1146/annurev.fluid.35.101101.161045

    Article  MathSciNet  MATH  Google Scholar 

  4. Ueno M, Kohzai M, Koga S, Kato H, Nakakita K, Sudani N, Nakamura Y (2015) Normalization of wind-tunnel data for NASA common research model. J Aircr 52(5):1535–1549. https://doi.org/10.2514/1.C032989

    Article  Google Scholar 

  5. Braslow AL, Knox EC (1958) Simplified method for determination of critical height of distributed roughness particles for boundary-layer transition at Mach numbers from 0 to 5. NACA TN-4363

  6. Holmes BJ, Obara CJ, Martin GL, Domack CS (1985) Manufacturing tolerances for natural laminar flow airframe surfaces. SAE Trans. https://doi.org/10.4271/850863

    Article  Google Scholar 

  7. Crouch JD, Kosorygin VS (2020) Surface step effects on boundary-layer transition dominated by Tollmien–Schlichting instability. AIAA J 58(7):2943–2950. https://doi.org/10.2514/1.J058518

    Article  Google Scholar 

  8. Von Doenhoff AE, Braslow AL (1961) The effect of distributed surface roughness on laminar flow. Bound Layer Flow Control. https://doi.org/10.1016/B978-1-4832-1323-1.50005-1

    Article  Google Scholar 

  9. De Vincentiis L, Henningson DS, Hanifi A (2022) Transition in an infinite swept-wing boundary layer subject to surface roughness and free-stream turbulence. J Fluid Mech. https://doi.org/10.1017/jfm.2021.962

    Article  MathSciNet  MATH  Google Scholar 

  10. Örlü R, Tillmark N, Alfredsson PH (2021) Measured critical size of roughness elements. Tech. Rep. KTH Royal Institute of technology. https://urldefense.com/v3/__. https://www.divaportal.org/smash/get/diva2:1538805/FULLTEXT01.pdf__;!!NLFGqXoFfo8MMQ!t27nE3QBTM4Ghn62pFZCIponJ8hLR0lA5x3xul5rWmsORu5Qp2EQCeE4MV6W2bdGBTbbidJ4n8aLFEwRjlsG2M-h_op7rwbifvR6_tY$. Accessed 19 Mar 2021

  11. Saric W, Carrillo Jr R, Reibert M (1998) Leading-edge roughness as a transition control mechanism. In: 36th AIAA aerospace sciences meeting and exhibit, pp 781. https://doi.org/10.2514/6.1998-781

  12. Ueno M, Koga S, Kohzai M, Yasue K, Kato H, Yamazaki W, Yamagishi S (2017) JAXA’s recent researches concerning Reynolds number effects on wind tunnel test of transonic transport aircraft. In: Proceedings of the 55th aircraft symposium, JSASS-2017-5119 in Japanese

  13. Kim JW (2007) Optimised boundary compact finite difference schemes for computational aeroacoustics. J Comput Phys 225(1):995–1019. https://doi.org/10.1016/j.jcp.2007.01.008

    Article  MathSciNet  MATH  Google Scholar 

  14. Kim JW (2010) High-order compact filters with variable cut-off wavenumber and stable boundary treatment. Comput Fluids 39(7):1168–1182. https://doi.org/10.1016/j.compfluid.2010.02.007

    Article  MATH  Google Scholar 

  15. Shima E, Kitamura K (2013) New approaches for computation of low Mach number flows. Comput Fluids 85:143–152. https://doi.org/10.1016/j.compfluid.2012.11.017

    Article  MathSciNet  MATH  Google Scholar 

  16. Vassberg J, Dehaan M, Rivers M, Wahls R (2008) Development of a common research model for applied CFD validation studies. In: 26th AIAA Applied Aerodynamics Conference, 6919. https://doi.org/10.2514/6.2008-6919

  17. Ishida T, Tsukahara T, Tokugawa N (2022) Parameter effects of spanwise-arrayed cylindrical roughness elements on transition in the Falkner–Skan–Cooke boundary layer. Trans Jpn Soc Aeronaut Space Sci 65(2):84–94. https://doi.org/10.2322/tjsass.65.84

    Article  Google Scholar 

  18. Jones LE, Sandberg RD, Sandham ND (2008) Direct numerical simulations of forced and unforced separation bubbles on an airfoil at incidence. J Fluid Mech 602:175–207. https://doi.org/10.1017/S0022112008000864

    Article  MATH  Google Scholar 

  19. Balakumar P (2017) Direct numerical simulation of flows over an NACA-0012 airfoil at low and moderate Reynolds numbers. In: 47th AIAA fluid dynamics conference, AIAA Paper 2017-3978. https://doi.org/10.2514/6.2017-3978

  20. Rizzetta DP, Visbal MR (2007) Direct numerical simulations of flow past an array of distributed roughness elements. AIAA J 45(8):1967–1976. https://doi.org/10.2514/1.25916

    Article  Google Scholar 

  21. Loiseau JC, Robinet JC, Cherubini S, Leriche E (2014) Investigation of the roughness-induced transition: global stability analyses and direct numerical simulations. J Fluid Mech 760:175–211. https://doi.org/10.1017/jfm.2014.589

    Article  MathSciNet  Google Scholar 

  22. Deyhle H, Bippes H (1996) Disturbance growth in an unstable three-dimensional boundary layer and its dependence on environmental conditions. J Fluid Mech 316:73–113. https://doi.org/10.1017/S0022112096000456

    Article  Google Scholar 

  23. Hashimoto A, Murakami K, Aoyama T, Ishiko K, Hishida M, Sakashita M, Lahur P (2012) Toward the fastest unstructured CFD code ‘FaSTAR.’ AIAA Paper. https://doi.org/10.2514/6.2012-1075

    Article  Google Scholar 

  24. Kohama Y, Onodera T, Egami Y (1996) Design and control of crossflow instability field. IUTAM symposium on nonlinear instability and transition in three-dimensional boundary layers, vol 35. Springer, Dordrecht. https://doi.org/10.1299/kikaib.63.849

  25. Fadlun EA, Verzicco R, Orlandi P, Mohd-Yusof J (2000) Combined immersed-boundary finite-difference methods for three-dimensional complex flow simulations. J Comput Phys 161(1):35–60. https://doi.org/10.1006/jcph.2000.6484

    Article  MathSciNet  MATH  Google Scholar 

  26. Högberg M, Henningson DS (1998) Secondary instability of cross-flow vortices in Falkner–Skan–Cooke boundary layers. J Fluid Mech 368:339–357. https://doi.org/10.1017/S0022112098001931

    Article  MathSciNet  MATH  Google Scholar 

  27. Brynjell-Rahkola M, Shahriari N, Schlatter P, Hanifi A, Henningson DS (2017) Stability and sensitivity of a cross-flow-dominated Falkner–Skan–Cooke boundary layer with discrete surface roughness. J Fluid Mech 826:830–850. https://doi.org/10.1017/jfm.2017.466

    Article  MathSciNet  MATH  Google Scholar 

  28. Bippes H (1999) Basic experiments on transition in three-dimensional boundary layers dominated by crossflow instability. Prog Aerosp Sci 35(4):363–412. https://doi.org/10.1016/S0376-0421(99)00002-0

    Article  Google Scholar 

  29. Deyhle H, Hohler G, Bippes H (1993) Experimental investigation of instability wave propagation in a three-dimensional boundary-layer flow. AIAA J 31(4):637–645. https://doi.org/10.2514/3.11597

    Article  Google Scholar 

Download references

Acknowledgements

The authors thank Dr. M. Ueno for valuable insights during the analysis of the NASA-CRM wing as well as Dr. Y. Aoki (JAXA) and Mr. O. Hamamura (IHI Aerospace Engineering) for extending their support during the wind tunnel tests. Moreover, the authors thank Dr. H. Abe (JAXA), Dr. H. Mamori (The University of Electro-Communications), and Dr. Y. Kametani (Meiji University) for extending their support and providing insight during development of our incompressible-fluid DNS code. Finally, the authors thank Dr. Y. Ide (JAXA) for the fruitful discussions concerning the instabilities observed in the three-dimensional boundary-layer flow. The wind tunnel test was performed with the cooperation of the JAXA Aeronautical Facility Research Unit. The compressible-fluid DNS analyses were performed using the computational resources of the JAXA Supercomputer System—generations 2 and 3 (JSS2 and JSS3).

Author information

Authors and Affiliations

  1. Japan Aerospace Exploration Agency, 6-13-1 Osawa, Mitaka-shi, Tokyo, 181-0015, Japan

    Takahiro Ishida & Naoko Tokugawa

  2. Ryoyu Systems Co. LTD., 6-19 Oe, Minato-ku, Nagoya-shi, Aichi, 455-0024, Japan

    Keisuke Ohira

  3. Tokyo University of Science, 2641 Yamazaki, Noda-shi, Chiba, 278-8510, Japan

    Rio Hosoi & Takahiro Tsukahara

Authors
  1. Takahiro Ishida
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Keisuke Ohira
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Rio Hosoi
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Naoko Tokugawa
    View author publications

    You can also search for this author in PubMed Google Scholar

  5. Takahiro Tsukahara
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Takahiro Ishida.

Ethics declarations

Conflict of interest

The authors declare no conflicts of interest associated with this manuscript.

Additional information

Publisher's Note

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

An earlier version of this paper was presented at APISAT 2021, Jeju, South Korea, in November 2021.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Ishida, T., Ohira, K., Hosoi, R. et al. Numerical and Experimental Analysis of Three-Dimensional Boundary-Layer Transition Induced by Isolated Cylindrical Roughness Elements. Int. J. Aeronaut. Space Sci. 23, 649–659 (2022). https://doi.org/10.1007/s42405-022-00485-0

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s42405-022-00485-0

Keywords

Search

Navigation