Skip to main content
SpringerLink
Log in

Direct numerical simulation of hypersonic transition induced by an isolated cylindrical roughness element

  • Article
  • Published:
Science China Physics, Mechanics & Astronomy Aims and scope Submit manuscript

Abstract

Hypersonic boundary layer transition induced by an isolated cylindrical roughness element is investigated using direct numerical simulation method based on a finite volume formulation. To simulate the transition procedure by resolving the generation and evolvement of small-scale coherent structures, and capture the shock wave at the same time, high-order minimum dispersion and controllable dissipation scheme is validated and then applied. The results are compared with the available measurements in the quiet wind tunnel, such as the dominated frequency and root mean square of pressure. The computational dominated frequency of 19.23 kHz is very close to the experimental one, 21 kHz. Also, the disturbances of the roughness are mostly generated by the “jet” just before the roughness, and then they travel and develop downstream with the shear layer and vortex shedding. The transition is mainly dominated by the instabilities of both the horseshoe vortex and the shear layer.

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

Access this article

Log in via an institution

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

Instant access to the full article PDF.

Institutional subscriptions

Similar content being viewed by others

References

  1. Whitehead A Jr. NASP aerodynamics. AIAA paper 1989–5013, 1989

    Google Scholar 

  2. van Driest E R, Blumer C B. Boundary-layer at supersonic speedsthree dimensional roughness effects (spheres). J Aero Sci, 1962, 29: 909–916

    Article  MATH  Google Scholar 

  3. Bertin J J, Stetson K F, Bouslog S A, et al. Effect of isolated roughness elements on boundary layer transition for shuttle orbiter. AIAA paper 1996-1906, 1996

    Google Scholar 

  4. Berry S A, Bouslog S A, Brauckmann G J, et al. Boundary layer transition due to isolated roughness-shuttle results from the LaRC 20-inch Mach 6 tunnel. AIAA paper 1997-273, 1997

    Google Scholar 

  5. Berry S A, Auslender A H, Dilley A D, et al. Hypersonic boundary layer trip development for Hyper-X. J Spacecraft Rockets, 2001, 38: 853–864

    Article  ADS  Google Scholar 

  6. Borg M P, Schneider S P. Effect of freestream noise on roughnessinduced transition for the X-51A forebody. J Spacecraft Rockets, 2008, 45: 1106–1116

    Article  ADS  Google Scholar 

  7. Danehy P M, Bathel B F, Ivey C B, et al. NO PLIF study of hypersonic transition over a discrete hemispherical roughness element. AIAA paper 2009-394, 2009

    Google Scholar 

  8. Danehy P M, Ivey C B, Inman J A, et al. High-speed PLIF imaging of hypersonic transition over discrete cylindrical roughness. AIAA paper 2010-703, 2010

    Google Scholar 

  9. Tirtey S C, Chazot O, Walpot L. Characterization of hypersonic roughness-induced boundary-layer transition. Exp Fluid, 2011, 50: 407–418

    Article  Google Scholar 

  10. Wheaton B M, Schneider S P. Roughness-induced instability in a hypersonic laminar boundary layer. AIAA J, 2012, 50: 1245–1256

    Article  ADS  Google Scholar 

  11. Wheaton B M, Schneider S P. Instability and transition due to near-critical roughness in a hypersonic laminar boundary layer. AIAA paper 2013-84, 2013

    Google Scholar 

  12. Li X L, Fu D X, Ma Y W. Direct numerical simulation of hypersonic boundary-layer transition over a blunt wedge (in Chinese). Sci China Ser G-Phys Mech Astron, 2004, 34: 466–480

    Google Scholar 

  13. Li X L, Fu D X, Ma Y W. Direct numerical simulation of hypersonic boundary-layer transition over a blunt cone. AIAA J, 2008, 46: 2899–2913

    Article  ADS  Google Scholar 

  14. Li X L, Fu D X, Ma Y W. Direct numerical simulation of hypersonic boundary-layer transition over a blunt cone with a small angle of attack. Phys Fluid, 2010, 22: 025105

    Article  ADS  Google Scholar 

  15. Dong M, Zhou H. A simulation on bypass transition and its key mechanism. Sci China-Phys Mech Astron, 2013, 56: 775–784

    Article  ADS  Google Scholar 

  16. Iyer P S, Muppidi S, Mahesh K. Transition of hypersonic flow past flat plate with roughness elements. AIAA paper 2010-5015, 2010

    Google Scholar 

  17. Iyer P S, Muppidi S, Mahesh K. Roughness-induced transition in high speed flows. AIAA paper 2011-566, 2011

    Google Scholar 

  18. Bernardini M, Pirozzoli S, Orlandi P. Compressibility effects on roughness-induced boundary layer transition. Int J Heat Fluid Flow, 2012, 35: 45–51

    Article  Google Scholar 

  19. Bartkowicz M D, Subbareddy P K, Candler G V. Numerical simulations of roughness induced instability in the Purdue Mach 6 wind tunnel. AIAA paper 2010-4723, 2010

    Google Scholar 

  20. Wheaton B M, Bartkowicz M D, Subbareddy P K, et al. Roughness-induced instabilities at Mach 6: A combined numerical and experimental study. AIAA paper 2011-3248, 2011

    Google Scholar 

  21. Yoon S, Barnhardt M D, Candler G V. Simulations of high-speed flow over an isolated roughness. AIAA paper 2010-1573, 2010

    Google Scholar 

  22. Duan Z W, Xiao Z X, Fu S. Simulation of transition triggered by isolated roughness in hypersonic boundary layer. AIAA paper 2012-3076, 2012

    Google Scholar 

  23. Serino G, Pinna F, Rambaud P. Numerical computations of hypersonic boundary layer roughness induced transition on a flat plate. AIAA paper 2012-568, 2012

    Google Scholar 

  24. Xiao Z X, Zhang M H, Xiao L H, et al. Studies of roughness-induced transition using three-equation k-ω-γ transition/turbulence model. AIAA paper 2013-3111, 2013

    Google Scholar 

  25. Xiao Z X, Liu J, Huang J B, et al. Numerical dissipation effects on the massive separation around tandem cylinders. AIAA J, 2012, 50: 1119–1136

    Article  ADS  Google Scholar 

  26. Xiao Z X, Liu J, Luo K Y, et al. Numerical investigation of massively separated flows past rudimentary landing gear using advanced DES approaches. AIAA J, 2013, 51: 107–125

    Article  ADS  Google Scholar 

  27. Huang J B, Xiao Z X, Liu J, et al. Simulation of shock wave buffet and its suppression on an OAT15A supercritical airfoil by IDDES. Sci China-Phys Mech Astron, 2012, 55: 260–271

    Article  ADS  Google Scholar 

  28. Sun Z S, Ren Y X, Larricq C, et al. A class of finite difference schemes with low dispersion and controllable dissipation for DNS of compressible turbulence. J Comput Phys, 2011, 230: 4616–4635

    Article  ADS  MATH  MathSciNet  Google Scholar 

  29. Wang Q J, Ren Y X, Sun Z S, et al. Low dispersion finite volume scheme based on reconstruction with minimized dispersion and controllable dissipation. Sci China-Phys Mech Astron, 2013, 56: 423–431

    Article  ADS  MathSciNet  Google Scholar 

  30. Jiang G S, Shu C W. Efficient implementation of weighted ENO schemes. J Comput Phys, 1996, 126: 202–228

    Article  ADS  MATH  MathSciNet  Google Scholar 

  31. Fu S, Xiao Z X, Chen H X, et al. Simulation of wing-body Junction flows with hybrid RANS/LES methods. Int J Heat Fluid Flow, 2007, 28: 1379–1390

    Article  Google Scholar 

  32. Bartkowicz M D. Numerical Simulations of Hypersonic Boundary Layer Transition. Dissertation for the Doctoral Degree. Minnesota: University of Minnesota, 2012

    Google Scholar 

Download references

Author information

Authors and Affiliations

  1. School of Aerospace, Tsinghua University, Beijing, 100084, China

    ZhiWei Duan, ZhiXiang Xiao & Song Fu

Authors
  1. ZhiWei Duan
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. ZhiXiang Xiao
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Song Fu
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to ZhiXiang Xiao.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Duan, Z., Xiao, Z. & Fu, S. Direct numerical simulation of hypersonic transition induced by an isolated cylindrical roughness element. Sci. China Phys. Mech. Astron. 57, 2330–2345 (2014). https://doi.org/10.1007/s11433-014-5556-4

Download citation

  • Received:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s11433-014-5556-4

Keywords

Search

Navigation