Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities

Roshan Sah; Sanchari Ghosh

doi:doi:10.11648/j.ijfmts.20210702.11

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Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities

Roshan Sah, Sanchari Ghosh

Published in International Journal of Fluid Mechanics & Thermal Sciences (Volume 7, Issue 2)

Received: 4 May 2021 Accepted: 28 May 2021 Published: 7 June 2021

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Abstract

The study of cavity flow is one of the most important research topics of unsteady aerodynamics. Supersonic turbulent flows over a cavity are mostly encountered in missiles, turbomachinery, and high-speed aircraft. The turbulence inside the cavity gives rise to excess drag, acoustic waves, pressure fluctuations, and vibrations which may lead to numerous problems like excess fuel consumption, failure of missile trajectory or mechanical parts, and aerodynamic heating. We conduct numerical simulations to investigate the flow and compare our results to existing experimental data to show quantitative validation. We then investigate the effect of the Mach number of the turbulent supersonic flow on the pressure contours and the vortical structures inside the cavity and the subsequent effect on other flow parameters like acoustic waves. Thereafter, we propose two modifications of the cavity geometry, a) slanted edges and b) smoothened corners with slanted edges, to improve the aerodynamic performance. ANSYS ICEM tool has been used for the fine mesh generation of our cavity geometry and all the simulation was run on ANSYS fluent software. The K-ω SST turbulence model was used for the simulation as it can capture the near-wall property with reasonable accuracy and a grid independence study was carried out to find the correct solution of the Navier-Stokes equation was proceeding by the solver. The parameters like pressure contours, streamline pattern, coefficient of pressure distribution and sound pressure level (SPL) has been found and compared for both modified and un-modified open cavity at different Mach number. The modifications suggested show a significant improvement over the open cavity designs in the mean pressure distribution and sound pressure level distributions.

Published in	International Journal of Fluid Mechanics & Thermal Sciences (Volume 7, Issue 2)
DOI	10.11648/j.ijfmts.20210702.11
Page(s)	12-21
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2021. Published by Science Publishing Group

Keywords

Cavity, Vorticity, Aspect ratio, Aerodynamic Characteristics Pressure Distribution, Mach Number, Supersonic Nomenclature

References

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[2]	Tracy, M. B., Plentovich, E. B. 1993, “Characterization of cavity flow fields using pressure date obtained in the Langley 0.3-meter transonic cryogenic tunnel,” NASA Tech. Memo. 4436.
[3]	Plentovich, E. B., Stallings, Robert L. Jr., M. B. Tracy. 1993, “Test cavity pressure measurements at subsonic and transonic speeds,”NASA Tech. Pap. 3358.
[4]	Dang Guo Yang, JianQiang Li, ZhaoLin Fan and Dan Yao. 2008, “Aerodynamic Characteristics of Transonic and Supersonic Flow over Rectangular Cavities.” Springer journal of Flow, Turbulence and Combustion Vol. 84, issue 4, pp 639-652.
[5]	Sridhar V, Gai S. L. and Kleine H. 2016,"Oscillatory Characteristics of Shallow Open Cavities in Supersonic Flow", AIAA Journal, Vol. 54, No. 11, pp. 3495-3508.
[6]	Rossiter, J., 1964, “Wind Tunnel Experiments on the Flow over Rectangular Cavities at Subsonic and Transonic Speeds,” Technical Report 64037 by Royal Aircraft Establishment
[7]	Rossiter, J., 1962, “The Effects Of Cavities On The Buffeting Of Aircraft” Technical Memorandum AERO. 754 by Royal Aircraft Establishment.
[8]	Rossiter J., 1960, “A Preliminary Investigation into Armament Bay Buffet at Subsonic and Transonic Speeds.” Technical Memorandum AERO 679 by Royal Aircraft Establishment.
[9]	Rossiter J., Kurn A., 1963, “A Wind Tunnel Measurements Of The Unsteady Pressures In And Behind A Bomb Bay, Technical Note AERO. 2677 by Royal Aircraft Establishment.
[10]	Bueno, P. C., Unalmis, Ö. H., Clemens, N. T., Dolling, D. S., 2002, “The Effects of Upstream Mass Injection on a Mach 2 Cavity Flow,” AIAA Journal.
[11]	Shieh M. C., Morris P., 2001, “Comparison of Two and Three Dimensional Turbulent Cavity Flows,” 39^th AIAA Aerospace Sciences Meeting and Exhibit.
[12]	Shih S. H., Hamed A., Yeuan J. J., 2004, “Unsteady Supersonic Cavity Flow Simulations Using Coupled k-ε and Navier- Stokes Equations,” AIAA Journal, Vol. 32, No. 10.
[13]	Rizetta, D. P., and Visbal, M. R., 2003 “Large Eddy Simulation of Supersonic Cavity Flowfields including Flow Control,” AIAA 41 (8).
[14]	Hamed, A., Basu, D., Das, K., 2003,“Effect of Reynolds Number On the Unsteady Flow and Acoustic Fields Of Supersonic Cavity,” Proceedings of FEDSM, ASME.
[15]	Aradag, S., Knight, D. D., 2004, “Simulation of supersonic cavity flow using 3DRANS equations,” AIAA Pap. 2004-4966.
[16]	Wilcox, D. C. 1993, “Turbulence Modeling for CFD,” DCW Industries, La Canada.
[17]	Wang, H., Sun, M., Qin, N. et al., “ Characteristics of Oscillations in Supersonic Open Cavity Flows”. Flow Turbulence Combust 90, 121–142 (2013). https://doi.org/10.1007/s10494-012-9434-8.
[18]	Wang H, Wang Z, Sun M, Qin N., “Experimental and numerical investigation of cavity-based supersonic flow and combustion”. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering. 2014; 228 (5): 781-798. doi: 10.1177/0954410013480300.
[19]	Zhaoxin Ren, Bing Wang, Bowen Hu, Longxi Zheng, “Numerical analysis of supersonic flows over an aft-ramped open-mode cavity”, Aerospace Science and Technology, Volume 78, 2018, Pages 427-437, ISSN 1270-9638, https://doi.org/10.1016/j.ast.2018.05.003.
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Roshan Sah, Sanchari Ghosh. (2021). Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities. International Journal of Fluid Mechanics & Thermal Sciences, 7(2), 12-21. https://doi.org/10.11648/j.ijfmts.20210702.11

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ACS Style

Roshan Sah; Sanchari Ghosh. Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities. Int. J. Fluid Mech. Therm. Sci. 2021, 7(2), 12-21. doi: 10.11648/j.ijfmts.20210702.11

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AMA Style

Roshan Sah, Sanchari Ghosh. Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities. Int J Fluid Mech Therm Sci. 2021;7(2):12-21. doi: 10.11648/j.ijfmts.20210702.11

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@article{10.11648/j.ijfmts.20210702.11,
  author = {Roshan Sah and Sanchari Ghosh},
  title = {Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities},
  journal = {International Journal of Fluid Mechanics & Thermal Sciences},
  volume = {7},
  number = {2},
  pages = {12-21},
  doi = {10.11648/j.ijfmts.20210702.11},
  url = {https://doi.org/10.11648/j.ijfmts.20210702.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijfmts.20210702.11},
  abstract = {The study of cavity flow is one of the most important research topics of unsteady aerodynamics. Supersonic turbulent flows over a cavity are mostly encountered in missiles, turbomachinery, and high-speed aircraft. The turbulence inside the cavity gives rise to excess drag, acoustic waves, pressure fluctuations, and vibrations which may lead to numerous problems like excess fuel consumption, failure of missile trajectory or mechanical parts, and aerodynamic heating. We conduct numerical simulations to investigate the flow and compare our results to existing experimental data to show quantitative validation. We then investigate the effect of the Mach number of the turbulent supersonic flow on the pressure contours and the vortical structures inside the cavity and the subsequent effect on other flow parameters like acoustic waves. Thereafter, we propose two modifications of the cavity geometry, a) slanted edges and b) smoothened corners with slanted edges, to improve the aerodynamic performance. ANSYS ICEM tool has been used for the fine mesh generation of our cavity geometry and all the simulation was run on ANSYS fluent software. The K-ω SST turbulence model was used for the simulation as it can capture the near-wall property with reasonable accuracy and a grid independence study was carried out to find the correct solution of the Navier-Stokes equation was proceeding by the solver. The parameters like pressure contours, streamline pattern, coefficient of pressure distribution and sound pressure level (SPL) has been found and compared for both modified and un-modified open cavity at different Mach number. The modifications suggested show a significant improvement over the open cavity designs in the mean pressure distribution and sound pressure level distributions.},
 year = {2021}
}

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TY  - JOUR
T1  - Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities
AU  - Roshan Sah
AU  - Sanchari Ghosh
Y1  - 2021/06/07
PY  - 2021
N1  - https://doi.org/10.11648/j.ijfmts.20210702.11
DO  - 10.11648/j.ijfmts.20210702.11
T2  - International Journal of Fluid Mechanics & Thermal Sciences
JF  - International Journal of Fluid Mechanics & Thermal Sciences
JO  - International Journal of Fluid Mechanics & Thermal Sciences
SP  - 12
EP  - 21
PB  - Science Publishing Group
SN  - 2469-8113
UR  - https://doi.org/10.11648/j.ijfmts.20210702.11
AB  - The study of cavity flow is one of the most important research topics of unsteady aerodynamics. Supersonic turbulent flows over a cavity are mostly encountered in missiles, turbomachinery, and high-speed aircraft. The turbulence inside the cavity gives rise to excess drag, acoustic waves, pressure fluctuations, and vibrations which may lead to numerous problems like excess fuel consumption, failure of missile trajectory or mechanical parts, and aerodynamic heating. We conduct numerical simulations to investigate the flow and compare our results to existing experimental data to show quantitative validation. We then investigate the effect of the Mach number of the turbulent supersonic flow on the pressure contours and the vortical structures inside the cavity and the subsequent effect on other flow parameters like acoustic waves. Thereafter, we propose two modifications of the cavity geometry, a) slanted edges and b) smoothened corners with slanted edges, to improve the aerodynamic performance. ANSYS ICEM tool has been used for the fine mesh generation of our cavity geometry and all the simulation was run on ANSYS fluent software. The K-ω SST turbulence model was used for the simulation as it can capture the near-wall property with reasonable accuracy and a grid independence study was carried out to find the correct solution of the Navier-Stokes equation was proceeding by the solver. The parameters like pressure contours, streamline pattern, coefficient of pressure distribution and sound pressure level (SPL) has been found and compared for both modified and un-modified open cavity at different Mach number. The modifications suggested show a significant improvement over the open cavity designs in the mean pressure distribution and sound pressure level distributions.
VL  - 7
IS  - 2
ER  -

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Author Information

Roshan Sah

Department of Aerospace Engineering, Indian Institute Of Technology Kharagpur, Kharagpur, India
Sanchari Ghosh

Department of Aerospace Engineering, Indian Institute Of Technology Kharagpur, Kharagpur, India

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APA Style

Roshan Sah, Sanchari Ghosh. (2021). Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities. International Journal of Fluid Mechanics & Thermal Sciences, 7(2), 12-21. https://doi.org/10.11648/j.ijfmts.20210702.11

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ACS Style

Roshan Sah; Sanchari Ghosh. Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities. Int. J. Fluid Mech. Therm. Sci. 2021, 7(2), 12-21. doi: 10.11648/j.ijfmts.20210702.11

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AMA Style

Roshan Sah, Sanchari Ghosh. Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities. Int J Fluid Mech Therm Sci. 2021;7(2):12-21. doi: 10.11648/j.ijfmts.20210702.11

Copy | Download

@article{10.11648/j.ijfmts.20210702.11,
  author = {Roshan Sah and Sanchari Ghosh},
  title = {Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities},
  journal = {International Journal of Fluid Mechanics & Thermal Sciences},
  volume = {7},
  number = {2},
  pages = {12-21},
  doi = {10.11648/j.ijfmts.20210702.11},
  url = {https://doi.org/10.11648/j.ijfmts.20210702.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijfmts.20210702.11},
  abstract = {The study of cavity flow is one of the most important research topics of unsteady aerodynamics. Supersonic turbulent flows over a cavity are mostly encountered in missiles, turbomachinery, and high-speed aircraft. The turbulence inside the cavity gives rise to excess drag, acoustic waves, pressure fluctuations, and vibrations which may lead to numerous problems like excess fuel consumption, failure of missile trajectory or mechanical parts, and aerodynamic heating. We conduct numerical simulations to investigate the flow and compare our results to existing experimental data to show quantitative validation. We then investigate the effect of the Mach number of the turbulent supersonic flow on the pressure contours and the vortical structures inside the cavity and the subsequent effect on other flow parameters like acoustic waves. Thereafter, we propose two modifications of the cavity geometry, a) slanted edges and b) smoothened corners with slanted edges, to improve the aerodynamic performance. ANSYS ICEM tool has been used for the fine mesh generation of our cavity geometry and all the simulation was run on ANSYS fluent software. The K-ω SST turbulence model was used for the simulation as it can capture the near-wall property with reasonable accuracy and a grid independence study was carried out to find the correct solution of the Navier-Stokes equation was proceeding by the solver. The parameters like pressure contours, streamline pattern, coefficient of pressure distribution and sound pressure level (SPL) has been found and compared for both modified and un-modified open cavity at different Mach number. The modifications suggested show a significant improvement over the open cavity designs in the mean pressure distribution and sound pressure level distributions.},
 year = {2021}
}

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TY  - JOUR
T1  - Numerical Investigation of Supersonic Turbulent Flow Over Open Cavities
AU  - Roshan Sah
AU  - Sanchari Ghosh
Y1  - 2021/06/07
PY  - 2021
N1  - https://doi.org/10.11648/j.ijfmts.20210702.11
DO  - 10.11648/j.ijfmts.20210702.11
T2  - International Journal of Fluid Mechanics & Thermal Sciences
JF  - International Journal of Fluid Mechanics & Thermal Sciences
JO  - International Journal of Fluid Mechanics & Thermal Sciences
SP  - 12
EP  - 21
PB  - Science Publishing Group
SN  - 2469-8113
UR  - https://doi.org/10.11648/j.ijfmts.20210702.11
AB  - The study of cavity flow is one of the most important research topics of unsteady aerodynamics. Supersonic turbulent flows over a cavity are mostly encountered in missiles, turbomachinery, and high-speed aircraft. The turbulence inside the cavity gives rise to excess drag, acoustic waves, pressure fluctuations, and vibrations which may lead to numerous problems like excess fuel consumption, failure of missile trajectory or mechanical parts, and aerodynamic heating. We conduct numerical simulations to investigate the flow and compare our results to existing experimental data to show quantitative validation. We then investigate the effect of the Mach number of the turbulent supersonic flow on the pressure contours and the vortical structures inside the cavity and the subsequent effect on other flow parameters like acoustic waves. Thereafter, we propose two modifications of the cavity geometry, a) slanted edges and b) smoothened corners with slanted edges, to improve the aerodynamic performance. ANSYS ICEM tool has been used for the fine mesh generation of our cavity geometry and all the simulation was run on ANSYS fluent software. The K-ω SST turbulence model was used for the simulation as it can capture the near-wall property with reasonable accuracy and a grid independence study was carried out to find the correct solution of the Navier-Stokes equation was proceeding by the solver. The parameters like pressure contours, streamline pattern, coefficient of pressure distribution and sound pressure level (SPL) has been found and compared for both modified and un-modified open cavity at different Mach number. The modifications suggested show a significant improvement over the open cavity designs in the mean pressure distribution and sound pressure level distributions.
VL  - 7
IS  - 2
ER  -

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