Abstract
A single ramp scramjet inlet is designed for operating at a Mach number of 5.96 and studied for subsonic bubble formation due to the shock wave–boundary layer interaction (SWBL). The Navier–Stokes computational fluid dynamics equation for ideal gas condition, with two-equation k–ω shear stress transport (SST) turbulence model, is solved using the RANS solver. The inlet designed with a ramp of 38.7° generates a strong shock wave made to impinge on the cowl generates a large separation bubble. The results obtained are validated with experimental results. Further, the inlet flow characteristics are analyzed under the unsteady condition to study the motion of the shock wave, variation of subsonic bubble size, the wall surface pressure fluctuation, and effect on mass flow due to the bubble size variation. Due to the shock wave–boundary layer interaction, the mass flow rate becomes unsteady in the core flow zone of the inlet.
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References
Deng, R., Jin, Y., Dong Kim, H.: Numerical simulation of the unstart process of dual-mode scramjet. Int. J. Heat Mass Transf. 105, 394–400 (2017)
Ben-Dor, G.: Shockwave Reflection Phenomena, 2nd edn. Springer (2007)
Tan, H., Sun, S.: Oscillatory flows of rectangular hypersonic inlet unstart caused by downstream mass-flow choking. J. Propul. Power 25(1) (2009)
Weixing, W., Rongwei, G.: Numerical study of unsteady starting characteristics of a hypersonic inlet. Chin. J. Aeronaut. 26(3), 563–577 (2013)
Van Wie, D.M., Aultt, D.A.: Internal flow field characteristics of a scramjet inlet at Mach 10. J. Propul. Power 12(1) (1996)
Barber, T.J., Hiett, D., Fastenberg, S.: CFD modeling of the hypersonic inlet starting problem. In: 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada (2006)
Schulte, D., Henckels, A., Wepler, U.: Reduction of shock induced boundary layer separation in hypersonic inlets using bleed. Aerosp. Sci. Technol. 4, 231–239 (1998)
John, B., Kulkarni, V.N., Natarajan, G.: Shock wave boundary layer interactions in hypersonic flows. Int. J. Heat Mass Transf. 70, 81–90 (2014)
Sriram, R.: Shock tunnel investigation on hypersonic impinging shockwave boundary layer interaction. PhD Thesis, Indian Institute of Science (2013)
Sriram, R., Jagadeesh, G.: Shock tunnel experiments on control of shock induced large separation bubble using boundary layer bleed. Aerosp. Sci. Technol. (2014)
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Raja Sekar, K., Jegadheeswaran, S., Kannan, R., Vadivelu, P., Prasad, G. (2019). Numerical Investigation of Single Ramp Scramjet Inlet Characteristics at Mach Number 5.96 Due to Shock Wave–Boundary Layer Interaction. In: Chandrasekhar, U., Yang, LJ., Gowthaman, S. (eds) Innovative Design, Analysis and Development Practices in Aerospace and Automotive Engineering (I-DAD 2018). Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-13-2697-4_20
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DOI: https://doi.org/10.1007/978-981-13-2697-4_20
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