Skip to main content
×
×
Home

Analysis of shock motion in shockwave and turbulent boundary layer interaction using direct numerical simulation data

  • MINWEI WU (a1) and M. PINO MARTÍN (a1)
Abstract

Direct numerical simulation data of a Mach 2.9, 24○ compression ramp configuration are used to analyse the shock motion. The motion can be observed from the animated DNS data available with the online version of the paper and from wall-pressure and mass-flux signals measured in the free stream. The characteristic low frequency is in the range of (0.007–0.013) U∞/δ, as found previously. The shock motion also exhibits high-frequency, of O(U∞/δ), small-amplitude spanwise wrinkling, which is mainly caused by the spanwise non-uniformity of turbulent structures in the incoming boundary layer. In studying the low-frequency streamwise oscillation, conditional statistics show that there is no significant difference in the properties of the incoming boundary layer when the shock location is upstream or downstream. The spanwise-mean separation point also undergoes a low-frequency motion and is found to be highly correlated with the shock motion. A small correlation is found between the low-momentum structures in the incoming boundary layer and the separation point. Correlations among the spanwise-mean separation point, reattachment point and the shock location indicate that the low-frequency shock unsteadiness is influenced by the downstream flow. Movies are available with the online version of the paper.

Copyright
References
Hide All
Andreopoulos, J. & Muck, K. C. 1987 Some new aspects of the shock-wave/boundary-layer interaction in compression-ramp flows. J. Fluid Mech. 180, 405428.
Beresh, S. J., Clemens, N. T. & Dolling, D. S. 2002 Relationship between upstream turbulent boundary-layer velocity fluctuations and separation shock unsteadiness. AIAA J. 40, 24122423.
Bookey, P. B., Wyckham, C., Smits, A. J. & Martin, M. P. 2005 New experimental data of STBLI at DNS/LES accessible Reynolds numbers. AIAA Paper 2005-309.
Dolling, D. S. & Or, C. T. 1985 Unsteadiness of the shock wave structure in attached and separated compression ramp flows. Exp. Fluids 3, 2432.
Dupont, P., Haddad, C. & Debiève, J. F. 2006 Space and time organization in a shock-induced separated boundary layer. J. Fluid Mech. 559, 255277.
Dussauge, J. P., Dupont, P. & Debiève, J. F. 2006 Unsteadiness in shock wave boundary layer interactions with separation. Aerospace Sci. Tech. 10 (2).
Eaton, J. K. & Johnston, J. P. 1981 Low-frequency unsteadiness of a reattaching turbulent shear layer. In Proc. 3rd Int. Symp. on Turbulent Shear Flow. Springer.
Erengil, M. E. & Dolling, D. S. 1991 Correlation of separation shock motion with pressure fluctuations in the incoming boundary layer. AIAA J. 29, 18681877.
Ganapathisubramani, B., Clemens, N. T. & Dolling, D. S. 2006 Large-scale motions in a supersonic turbulent boundary layer. J. Fluid Mech. 556, 271282.
Ganapathisubramani, B., Clemens, N. T. & Dolling, D. S. 2007 a Effects of upstream boundary layer on the unsteadiness of shock induced separation. J. Fluid Mech. 585, 369394.
Ganapathisubramani, B., Clemens, N. T. & Dolling, D. S. 2007 b Effects of upstream coherent structures on low-frequency motion of shock-induced turbulent separation. AIAA Paper. 2007-1141.
Gharib, M. & Roshko, A. 1987 The effect of flow oscillations on cavity drag. J. Fluid Mech. 177, 501530.
Hutchins, N. & Marusic, I. 2007 Evidence of very long meandering features in the logarithmic region of turbulent boundary layers. J. Fluid Mech. 579, 128.
Owen, F. K. & Horstmann, C. C. 1972 On the structure of hypersonic turbulent boundary layers. J. Fluid Mech. 53, 611636.
Pirozzoli, S. & Grasso, F. 2006 Direct numerical simulation of impinging shock wave/turbulent boundary layer interaction at M = 2.25. Phys. Fluids 18.
Plotkin, K. J. 1975 Shock wave oscillation driven by turbulent boundary-layer fluctuations. AIAA J. 13, 10361040.
Ringuette, M. J., Wu, M. & Martin, M. P. 2008 Coherent structures in direct numerical simulation of supersonic turbulent boundary layers at Mach 3. J. Fluid Mech. 594, 5969.
Rowley, C. W., Colonius, T. & Basu, A. J. 2002 On self-sustained oscillation in two-dimensional compressible flow over rectangular cavities. J. Fluid Mech. 455, 315346.
Samimy, M., Arnette, S. A. & Elliott, G. S. 1994 Streamwise structures in a turbulent supersonic boundary layer. Phys. Fluids 6, 10811083.
Selig, M. S. 1988 Unsteadiness of shock wave/turbulent boundary layer interactions with dynamic control. PhD thesis, Princeton University.
Simpson, R. L. 1989 Turbulent boundary-layer separation. Ann. Rev. Fluid Mech. 21, 205234.
Thomas, F. O., Putnam, C. M. & Chu, H. C. 1994 One the mechanism of unsteady shock oscillation in shock wave/turbulent boundary layer interactions. Exps. Fluids 18, 6981.
Wu, M. & Martin, M. P 2007 Direct numerical simulation of shockwave and turbulent boundary layer interaction induced by a compression Ramp. AIAA J. 45, 879889.
Wu, P. 2000 MHz-rate pulse-burst laser imaging system: development and application in the high-speed flow diagnostics. PhD thesis, Princeton University.
Wu, P. & Miles, R. B. 2001 Megahertz visualization of compression-corner shock structures. AIAA J. 39, 15421546.
Recommend this journal

Email your librarian or administrator to recommend adding this journal to your organisation's collection.

Journal of Fluid Mechanics
  • ISSN: 0022-1120
  • EISSN: 1469-7645
  • URL: /core/journals/journal-of-fluid-mechanics
Please enter your name
Please enter a valid email address
Who would you like to send this to? *
×
MathJax

JFM classification

Type Description Title
VIDEO
Movies

Wu and Martin supplementary movie
Movie 2. This movie shows a plan-view (top-view) of the 24-degree compression ramp interaction with Mach number 3 and Reyonlds number based on the momentum thickness of the incoming boundary layer 2300. The plan is at a wall-normal location of 0.9 delta away from the wall, where delta is the incoming boundary layer thickness. Flow is from left to right. Contours of the magnitude of the pressure gradient is shown to visualize the spanwise wrinkling shock motion. Data rate is 100 kHz (or 1 Uinf/delta). The frequency of the spanwise wrinkling shock motion is seen to be of order 1 Uinf/delta with a magnitude of about 0.5 delta.

 Video (4.6 MB)
4.6 MB
VIDEO
Movies

Wu and Martin supplementary movie
Movie 1. This movie shows a three-dimensional view of the 24-degree compression ramp interaction with Mach number 3 and Reyonlds number based on the momentum thickness of the incoming boundary layer 2300. Flow is from lower-left to upper-right. Iso-surface of the magnitude of the pressure gradient is shown to visualize the shock. Data rate is 100 kHz (or 1 Uinf/delta, where delta is the incoming boundary layer thickness). The black triangle in the movie is a reference point to see the streamwise shock motion. The relatively high-frequency spanwise wrinkling motion of the shock near the shock foot region and the low-frequency streamwise shock oscillation is seen.

 Video (8.3 MB)
8.3 MB

Metrics

Full text views

Total number of HTML views: 0
Total number of PDF views: 0 *
Loading metrics...

Abstract views

Total abstract views: 0 *
Loading metrics...

* Views captured on Cambridge Core between <date>. This data will be updated every 24 hours.

Usage data cannot currently be displayed