Microvortex Generator Controlled Shock–Boundary Layer Interactions in Hypersonic Intake
Publication: Journal of Aerospace Engineering
Volume 34, Issue 2
Abstract
The occurrence of shock and boundary layer interactions (SBLIs) in aircraft-engine intakes often results in poor total pressure recovery, a degraded boundary layer, and, in worst cases, flow separation. Hence, the SBLIs must be controlled to reduce/eliminate the losses. In this study, the efficacy of conventional microvortex generators (MVGs), deployed before and at the interaction region of a Mach 5.7 mixed-compression intake, has been investigated experimentally. Specifically, an array of MVGs, placed in the spanwise direction, was found to be useful in reducing the extent of the interactions. The height of the MVGs was varied as 0.5, 0.7, and 1 mm. Both quantitative and qualitative investigations have been carried out by measuring the static pressure distribution over the surface of the ramp and visualizing the SBLI phenomena at various time instants during the test run using the time-resolved Schlieren technique. The MVGs with a height of 1.0 mm, deployed at the interaction region, appeared to be quite effective in reducing the wall static pressure, with a maximum of a 13.57% reduction at the downstream proximal location. In addition, the Schlieren images show a decrease in the separation bubble size in all the intakes controlled with MVGs; a maximum reduction of 31.25% in the bubble length is achieved with 0.7 mm MVGs, which is deployed upstream of the interaction point.
Get full access to this article
View all available purchase options and get full access to this article.
Data Availability Statement
All data, models, and code generated or used during the study appear in the published article.
Acknowledgments
The authors acknowledge the Indian Institute of Science Bangalore for providing the hypersonic shock tube facility to carry out the experiments. The authors deeply acknowledge the financial support provided by the Science and Engineering Research Board, which helped immensely in completing the study (Grant No. EMR/2016/000506).
References
Anderson, B., J. Tinapple, and L. Surber. 2006. “Optimal control of shock wave turbulent boundary layer interactions using micro-array actuation.” In Proc., 3rd AIAA Flow Control Conf. Washington, DC: American Institute of Aeronautics and Astronautics.
Ashill, P., J. Fulker, and K. Hackett. 2001. “Research at DERA on sub boundary layer vortex generators (SBVGs).” In Proc., 39th Aerospace Sciences Meeting and Exhibit. Washington, DC: American Institute of Aeronautics and Astronautics.
Babinsky, H., and J. K. Harvey. 2011. Shock-wave boundary-layer interactions. Cambridge, UK: Cambridge University Press.
Babinsky, H., Y. Li, and C. W. Pitt-Ford. 2009. “Micro-ramp control of supersonic oblique shock-wave/boundary-layer interactions.” AIAA J. 47 (3): 668–675. https://doi.org/10.2514/1.38022.
Brown, A. C., H. F. Nawrocki, and P. N. Paley. 1968. “Subsonic diffusers designed integrally with vortex generators.” J. Aircr. 5 (3): 221–229. https://doi.org/10.2514/3.43931.
Delery, J. 1985. “Shock wave/turbulent boundary layer interaction and its control.” Prog. Aerosp. Sci. 22 (4): 209–280. https://doi.org/10.1016/0376-0421(85)90001-6.
Delery, J., and J. G. Marvin. 1986. Shock-wave boundary layer interactions. Cambridge, UK: Cambridge University Press.
Estruch-Samper, D., L. Vanstone, R. Hillier, and B. Ganapathisubramani. 2015. “Micro vortex generator control of axisymmetric high-speed laminar boundary layer separation.” Shock Waves 25 (5): 521–533. https://doi.org/10.1007/s00193-014-0514-7.
Giepman, R. H. M., F. F. J. Schrijer, and B. W. van Oudheusden. 2014. “Flow control of an oblique shock wave reflection with micro-ramp vortex generators: Effects of location and size.” Phys. Fluids 26 (6): 066101. https://doi.org/10.1063/1.4881941.
Goldsmith, E. L., and J. Seddon. 1993. Practical intake aerodynamic design. 2nd ed. Washington, DC: American Institute of Aeronautics and Astronautics.
Holden, H., and H. Babinsky. 2007. “Effect of micro-vortex generators on separated normal shock/boundary layer interactions.” J. Aircr. 44 (1): 170–174. https://doi.org/10.2514/1.22770.
Huang, W., H. Wu, Y.-G. Yang, L. Yan, and S.-B. Li. 2020. “Recent advances in the shock wave/boundary layer interaction and its control in internal and external flows.” Acta Astronaut. 174 (Sep): 103–122. https://doi.org/10.1016/j.actaastro.2020.05.001.
Idris, A. C., M. R. Saad, H. Zare-Behtash, and K. Kontis. 2014. “Luminescent measurement systems for the investigation of a scramjet inlet-isolator.” Sensors 14 (4): 6606–6632. https://doi.org/10.3390/s140406606.
Inger, G., and T. Siebersma. 1989. “Computational simulation of vortex generator effects on transonic shock/boundary-layer interaction.” J. Aircr. 26 (8): 697–698. https://doi.org/10.2514/3.45826.
Kaushik, M. 2012. Innovative passive control techniques for supersonic jet mixing. 1st ed. Saarbrücken, Germany: Lambert Academic Publishing.
Kaushik, M. 2019. “Experimental studies on micro-vortex generator controlled shock/boundary-layer interactions in Mach 2.2 intake.” Int. J. Aeronaut. Space Sci. 20 (3): 584–595. https://doi.org/10.1007/s42405-019-00166-5.
Lin, J. C. 1999. “Control of turbulent boundary-layer separation using micro-vortex generators.” In Proc., 30th AIAA Fluid Dynamics Conf. Washington, DC: American Institute of Aeronautics and Astronautics.
Lin, J. C. 2002. “Review of research on low-profile vortex generators to control boundary-layer separation.” Prog. Aerosp. Sci. 38 (4–5): 389–420. https://doi.org/10.1016/S0376-0421(02)00010-6.
Lin, J. C., F. G. Howard, D. M. Bushnell, and G. V. Selby. 1990. “Investigation of several passive and active methods for turbulent flow separation control.” In Proc., 21st Fluid Dynamics, Plasma Dynamics and Lasers Conf. Washington, DC: American Institute of Aeronautics and Astronautics.
Lu, F. K., Q. Li, and C. Liu. 2012. “Microvortex generators in high speed flow.” Prog. Aerosp. Sci. 53 (Aug): 30–45. https://doi.org/10.1016/j.paerosci.2012.03.003.
Macheret, S. O., M. N. Shneider, and R. B. Miles. 2007. “Optimum performance of electron beam driven magneto hydrodynamic generators for scramjet inlet control.” AIAA J. 45 (9): 2157–2163. https://doi.org/10.2514/1.16955.
McCormick, D. C. 1993. “Shock/boundary-layer interaction control with vortex generators and passive cavity.” AIAA J. 31 (1): 91–96. https://doi.org/10.2514/3.11323.
Panaras, A. G., and F. K. Lu. 2015. “Micro-vortex generators for shock wave/boundary layer interactions.” Prog. Aerosp. Sci. 74 (Dec): 16–47. https://doi.org/10.1016/j.paerosci.2014.12.006.
Pearcey, H. 1961. “Boundary layer control for aerofoils and wings.” In Vol. 2 of Boundary layer and flow control: Its principles and application, edited by G. Lachmann, 1261–1333. Oxford: Pergamon Press.
Rao, D. M., and T. T. Kariya. 1988. “Boundary-layer submerged vortex generators for separation control—An exploratory study.” In Proc., 1st National Fluid Dynamics Congress, Washington, DC: American Institute of Aeronautics and Astronautics.
Saad, M. R., H. Zare-Behtash, A. Che-Idris, and K. Kontis. 2012. “Micro-ramps for hypersonic flow control.” Micromachines 3 (2): 364–378. https://doi.org/10.3390/mi3020364.
Schulte, D., A. Henckles, and U. Wepler. 1998. “Reduction of shock induced boundary layer separation in hypersonic inlets using bleed.” Aerosp. Sci. Technol. 2 (4): 231–239. https://doi.org/10.1016/S1270-9638(98)80001-1.
Smart, M. 2010. Scramjet inlets. Brisbane, Australia: Center for Hypersonics, The Univ. of Queensland.
Sriram, R., and G. Jagadeesh. 2014. “Shock tunnel experiments on control of shock induced large separation bubble using boundary layer bleed.” Aerosp. Sci. Technol. 36 (Jul): 87–93. https://doi.org/10.1016/j.ast.2014.04.003.
Titchener, N., and H. Babinsky. 2009. “Shock wave/boundary-layer interaction control using a combination of vortex generators and bleed.” AIAA J. 51 (5): 1221–1233. https://doi.org/10.2514/1.J052079.
Xie, W. Z., Z. M. Wu, A. Y. Yu, and S. Guo. 2017. “Control of severe shock-wave/boundary-layer interactions in hypersonic inlets.” J. Propul. Power 34 (Oct): 614–623.
Yan, L., H. Wu, W. Huang, S-B. Li, and J. Liu. 2020. “Shock wave/turbulence boundary layer interaction control with the secondary recirculation jet in a supersonic flow.” Acta Astronaut. 173 (Apr): 131–138. https://doi.org/10.1016/j.actaastro.2020.04.003.
Zhang, Y., H.-J. Tan, M.-C. Du, and D.-P. Wang. 2015. “Control of shock/boundary-layer interaction for hypersonic inlets by highly swept microramps.” J. Propul. Power 31 (1): 133–143. https://doi.org/10.2514/1.B35299.
Zhang, Y., H.-J. Tan, F.-C. Tian, and Y. Zhuang. 2014. “Control of incident shock/boundary-layer interaction by a two-dimensional bump.” AIAA J. 52 (4): 767–776. https://doi.org/10.2514/1.J052786.
Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 34 • Issue 2 • March 2021
Copyright
© 2020 American Society of Civil Engineers.
History
Received: Oct 15, 2019
Accepted: Oct 9, 2020
Published online: Dec 31, 2020
Published in print: Mar 1, 2021
Discussion open until: May 31, 2021
Authors
Metrics & Citations
Metrics
Citations
Download citation
If you have the appropriate software installed, you can download article citation data to the citation manager of your choice. Simply select your manager software from the list below and click Download.