Unstart/Restart Boundary Broadening Method for a Two-Dimensional Supersonic Variable Inlet Based on a Distributed Bleed System
Publication: Journal of Aerospace Engineering
Volume 36, Issue 1
Abstract
Compared to the fixed-geometry inlet, the supersonic variable inlet improves its wide Mach number operating capability and efficient cruise property, mainly by regulating the throat area. However, the magnitude of its performance improvement is constrained by the unstart and restart boundaries. To broaden the operating boundaries of the inlet, a distributed bleed system capable of suppressing the shock-dominated internal flow was developed. Its control effect and influence mechanism were investigated by an unsteady numerical simulation with a dynamic grid technique at freestream Mach numbers of 2.5, 3.0, 3.5, and 4.0. The results indicate that the proposed distributed bleed system can adaptively tune the bleed ratio to maintain the dynamic stability of the inlet’s flowfield according to the varying wave system in the internal duct. Additionally, the inlet’s unstart and restart boundaries were significantly improved. The unstart internal contraction ratio (defined as the area ratio of the duct entrance and throat, denoted as ICR) increased from 1.96 to 2.18, and the restart ICR increased from 1.37 to 1.47 when the freestream Mach number was 3.0. The mechanism of improving the unstart boundary is that the distributed bleed system alters the boundary-layer characteristics of the bleed region, making it thinner and fuller, with stronger resistance to reverse pressure gradients. The mechanism of improving the restart boundary is that the distributed bleed system reduces the spillage by increasing the inlet’s throat flow capacity, making the separation shock at the duct entrance impinge earlier on the cowl lip than that of the uncontrolled inlet. Moreover, the control effects of the distributed bleed system at different bleed ratios and under a wide Mach number range were investigated, which will provide guidance for practical engineering design and application.
Get full access to this article
View all available purchase options and get full access to this article.
Data Availability Statement
The data or model used to support the findings of this study are available from the corresponding author upon request.
Acknowledgments
This work is cofunded by the National Natural Science Foundation of China (Grant Nos. U20A2070, 12025202, and 12172175) and the National Science and Technology Major Project (Grant No. J2019-II-0014-0035). We thank the valuable comments and suggestions from the editorial committee and reviewers. We thank the journal production team for arranging the production process. We also thank Ying Chen for her valuable work in checking and revising the manuscript.
References
Babinsky, H., and J. K. Harvey. 2011. Shock-wave boundary-layer interactions. New York: Cambridge University Press.
Benson, D. B., T. I. P. Shih, and D. O. Davis. 2003. “CFD simulations of an axisymmetric mixed-compression inlet with bleed through discrete holes.” In Proc., 4th ASME/FED and JSME 2003 Joint Fluids Conf. Reston, VA: ASME.
Chen, H., H. J. Tan, Y. Z. Liu, and Q. F. Zhang. 2019. “External-compression supersonic inlet free from violent buzz.” AIAA J. 57 (6): 2513–2523. https://doi.org/10.2514/1.J057811.
Choe, Y., C. Kim, and K. Kim. 2020. “Effects of optimized bleed system on supersonic inlet performance and buzz.” J. Propul. Power 36 (2): 211–222. https://doi.org/10.2514/1.B37474.
Curran, E. T., and S. N. B. Murthy. 2001. Scramjet propulsion. Reston, VA: AIAA Education Series.
Delery, J. M. 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.
Do, H., S. Im, M. G. Mungal, and M. A. Cappelli. 2011. “The influence of boundary layers on supersonic inlet unstart.” In Proc., 17th AIAA Int. Space Planes and Hypersonic Systems and Technologies Conf. Reston, VA: American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.2011-2349.
Erdem, E., K. Kontis, E. Johnstone, N. P. Murray, and J. Steelant. 2013. “Experiments on transitional shock wave–boundary layer interactions at Mach 5.” Exp. Fluids 54 (10): 1–22. https://doi.org/10.1007/s00348-013-1598-z.
Falempin, F., E. Wendling, M. Goldfeld, and A. Syarov. 2006. “Experimental investigation of starting process for a variable geometry air inlet operating from Mach 2 to Mach 8.” In Proc., 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conf. and Exhibit. Reston, VA: American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.2006-4513.
Fukuda, M. K., W. R. Hingst, and E. Reshotko. 1977. “Bleed effects on shock boundary-layer interactions in supersonic mixed compression inlets.” J. Aircr. 14 (2): 151–156. https://doi.org/10.2514/3.58756.
Gnani, F., H. Zare-Bahtash, and K. Kontis. 2016. “Pseudo-shock waves and their interactions in high-speed intakes.” Prog. Aerosp. Sci. 82 (Apr): 36–56. https://doi.org/10.1016/j.paerosci.2016.02.001.
Gnani, F., H. Zare-Bahtash, C. White, and K. Kontis. 2018. “Effect of back-pressure forcing on shock train structures in rectangular channels.” Acta Astronaut. 145 (Apr): 471–481. https://doi.org/10.1016/j.actaastro.2018.02.010.
Herrmann, D., S. Blem, and A. Gülhan. 2011. “Experimental study of boundary-layer bleed impact on ramjet inlet performance.” J. Propul. Power 27 (6): 1186–1195. https://doi.org/10.2514/1.B34223.
Herrmann, D., and A. Gülhan. 2015. “Experimental analyses of inlet characteristics of an airbreathing missile with boundary-layer bleed.” J. Propul. Power 31 (1): 170–179. https://doi.org/10.2514/1.B35339.
Hong, W., and C. Kim. 2014. “Computational study on hysteretic inlet buzz characteristics under varying mass flow conditions.” AIAA J. 52 (7): 1357–1373. https://doi.org/10.2514/1.J052481.
Idris, A. C., M. R. Saad, H. Zare-Bahtash, 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.
Jiao, X. L., J. T. Chang, Z. Q. Wang, and D. R. Yu. 2016. “Hysteresis phenomenon of hypersonic inlet at high Mach number.” Acta Astronaut. 128 (Nov–Dec): 657–668. https://doi.org/10.1016/j.actaastro.2016.08.025.
Jin, Y., S. Sun, H. J. Tan, Y. Zhang, and H. X. Huang. 2022a. “Flow response hysteresis of throat regulation process of a two-dimensional mixed-compression supersonic inlet.” Chin. J. Aeronaut. 35 (3): 112–127. https://doi.org/10.1016/j.cja.2021.06.013.
Jin, Y., S. Sun, Y. Zhang, F. Xing, and H. J. Tan. 2022b. “Throttling characteristics of a supersonic variable inlet at different internal contraction ratios.” AIAA J. 60 (9): 5203–5241. https://doi.org/10.2514/1.J061685.
Jin, Y., Y. Zhang, H. J. Tan, X. Li, S. Sun, and D. P. Wang. 2022c. “Oscillations in rectangular supersonic inlets with large internal contraction ratio.” AIAA J. 60 (8): 4628–4638. https://doi.org/10.2514/1.J061353.
Kantrowitz, A., and C. D. Donaldson. 1945. Preliminary investigation of supersonic diffuser. Washington, DC: The National Aeronautics and Space Administration.
Menter, F. R. 1994. “Two-equation eddy-viscosity turbulence models for engineering applications.” AIAA J. 32 (8): 1598–1605. https://doi.org/10.2514/3.12149.
Menter, F. R., M. Kuntz, and R. Langtry. 2003. “Ten years of industrial experience with the SST turbulence model.” Heat Mass Transfer 4 (1): 625–632.
Obery, L. J., and R. W. Cubbison. 1954. Effectiveness of boundary-layer removal near throat of ramp-type side inlet at freestream Mach number of 2.0. Washington, DC: NASA.
Paynter, G. C., D. W. Mayer, and E. Tjonneland. 1993. “Flow stability issues in supersonic inlet flow analyses.” In Proc., 31st Aerospace Sciences Meeting and Exhibit. Reston, VA: American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.1993-290.
Roe, P. L. 1981. “Approximate Riemann solvers, parameter vectors, and difference schemes.” J. Comput. Phys. 43 (2): 357–372. https://doi.org/10.1016/0021-9991(81)90128-5.
Roy, C. J., and F. G. Blottner. 2003. “Methodology for turbulence model validation: Application to hypersonic flows.” J. Spacecr. Rockets 40 (3): 313–325. https://doi.org/10.2514/2.3966.
Sanders, B. W., and R. W. Cubbison. 1968. Effect of bleed-system back pressure and porous area on the performance of an axisymmetric mixed compression inlet at Mach 2.5. Washington, DC: NASA.
Sanders, B. W., and G. A. Mitchell. 1970. “Increasing the stable operating range of a Mach 2.5 inlet.” In Proc., AIAA 6th Propulsion Joint Specialist Conf. Reston, VA: American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.1970-686.
Sanders, B. W., and L. J. Weir. 2008. Aerodynamic design of a dual-flow Mach 7 hypersonic inlet system for a turbine-based combined-cycle hypersonic propulsion system. Washington, DC: NASA.
Scherrer, R., and W. E. Anderson. 1958. Investigation of the performance and internal flow of a variable-area, variable-internal-contraction inlet at Mach numbers of 2.00, 2.50, and 2.92. Washington, DC: NASA.
Scherrer, R., and F. E. Gowen. 1955. Preliminary experimental investigation of a variable-area, variable-internal-contraction air inlet at Mach numbers between 1.42 and 2.44. Washington, DC: NASA.
Slater, J. W. 2012. “Improvements in modeling 90-degree bleed holes for supersonic inlets.” J. Propul. Power 28 (4): 773–781. https://doi.org/10.2514/1.B34333.
Soltani, M. R., A. Daliri, J. S. Younsi, and M. Farahani. 2016. “Effects of bleed position on the stability of a supersonic inlet.” J. Propul. Power 32 (5): 1153–1166. https://doi.org/10.2514/1.B36162.
Soltani, M. R., J. S. Younsi, and M. Farahani. 2015. “Effects of boundary-layer bleed parameters on supersonic intake performance.” J. Propul. Power 31 (3): 826–836. https://doi.org/10.2514/1.B35461.
Syberg, J., and J. L. Koncsek. 1976. “Experimental evaluation of an analytically derived bleed system for a supersonic inlet.” J. Aircr. 13 (10): 792–797. https://doi.org/10.2514/3.58712.
Taguchi, H., and R. Yanagi. 1998. “A study on pre-cooled turbojet-scramjet-rocket combined engines.” In Proc., 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. and Exhibit. Reston, VA: American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.1998-3777.
Teh, E. J., and T. I. P. Shih. 2013. “Reynolds-averaged simulations of shock-wave/boundary-layer interactions with bleed.” In Proc., 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, VA: American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.2013-423.
Timofeev, E. V., R. B. Tahir, and S. Mölder. 2008. “On recent developments related to flow starting in hypersonic air intakes.” In Proc., 15th AIAA Int. Space Planes and Hypersonic Systems and Technologies Conf. Reston, VA: American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.2008-2512.
Van Leer, B. 1979. “Towards the ultimate conservative difference scheme. V. A. second order sequel to Godunov’s method.” J. Comput. Phys. 32 (1): 101–136. https://doi.org/10.1016/0021-9991(79)90145-1.
Van Wie, D. M., F. T. Kwok, and R. F. Walsh. 1996. “Starting characteristics of supersonic inlets.” In Proc., 32nd AIAA/ASME/SAE/ASEE Joint Propulsion Conf. and Exhibit. Reston, VA: American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.1996-2914.
Wagner, J. L., A. Valdivia, K. Yuceil, N. T. Clemens, and D. S. Dolling. 2007. “An experimental investigation of supersonic inlet unstart.” In Proc., 37th AIAA Fluid Dynamics Conf. and Exhibit. Reston, VA: American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.2007-4352.
Wang, C. P., X. Yang, L. S. Xue, K. Kontis, and Y. Jiao. 2019. “Correlation analysis of separation shock oscillation and wall pressure fluctuation in unstarted hypersonic inlet flow.” Aerospace 6 (1): 8. https://doi.org/10.3390/aerospace6010008.
Wang, D. P., Y. Zhuang, H. J. Tan, H. Zhang, M. C. Du, and G. S. Li. 2015. “Design and simulation of a dual-channel variable geometry tur-bine based combined cycle inlet.” J. Aerosp. Power 30 (11): 2695–2704.
Wang, W. X., and R. W. Guo. 2013. “Numerical study of unsteady starting characteristics of a hypersonic inlet.” Chin. J. Aeronaut. 26 (3): 563–571. https://doi.org/10.1016/j.cja.2013.04.018.
White, F. M. 2006. Viscous fluid flow. 3rd ed. New York: McGraw-Hill.
Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 36 • Issue 1 • January 2023
Copyright
© 2022 American Society of Civil Engineers.
History
Received: Apr 12, 2022
Accepted: Sep 7, 2022
Published online: Nov 1, 2022
Published in print: Jan 1, 2023
Discussion open until: Apr 1, 2023
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.