Abstract
A parametric study of multiple shock wave boundary layer interactions is presented in this paper. All results were obtained using the computational fluid dynamics solver of Glasgow University. Such interactions often occur in high-speed intakes, depending on the state of the upstream boundary layer, and can adversely affect the performance of the intake. First, RANS simulations with a Reynolds-stress based turbulence model of multiple shock wave boundary layer interaction in a rectangular duct were performed and compared to the experiments followed by simulations at different Mach and Reynolds numbers and flow confinement levels. The results showed that Reynolds-stress based turbulence models can predict the interaction well. The employed explicit algebraic Reynolds stress model showed good agreement for the corner and centreline separations and resulted only in a small underprediction of the wall pressure. Flow distortion and total pressure recovery efficiency metrics were defined and evaluated for each interaction. Lower upstream Mach number and/or lower levels of flow confinement were required to achieve higher total pressure recoveries and lower flow distortion levels.
This is a preview of subscription content, log in via an institution to check access.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
References
Axelsson O (1994) Iterative solution methods. Cambridge University Press
Boychev K, Barakos GN, Steijl R (2020) Flow physics and sensitivity to RANS modelling assumptions of a multiple shock wave/turbulent boundary layer interaction. Aerosp Sci Technol 97(1)
Bruce PJK, Babinsky H, Tartinville B, Hirsch C (2011) Corner effect and asymmetry in transonic channel flows. AIAA J 49(11):2382–2392
Carroll BF (1988) Numerical and experimental investigation of multiple shock wave/turbulent boundary layer interactions in a rectangular duct. PhD thesis, University of Illinois at Urbana-Champaign, Urbana, IL
Carroll BF, Dutton JC (1989) An LDV investigation of a multiple normal shock wave/turbulent boundary layer interaction. In: 27th aerospace sciences meeting
Carroll BF, Dutton JC (1992) Characteristics of multiple shock wave/turbulent boundary-layer interactions in rectangular ducts. J Propuls Power 8(2):441–448
Carroll BF, Dutton JC (1992) Multiple normal shock wave/turbulent boundary-layer interactions. J Propuls Power 8(2):441–448
Carroll BF, Dutton JC (1992) Multiple normal shock wave/turbulent boundary-layer interactions. AIAA J 30(1):43–48
Carroll BF, Lopez-Fernandez PA, Dutton JC (1993) Computations and experiments for a multiple normal shock/boundary-layer interaction. J Propuls Power 9(3):405–411
Doerffer P, Hirsch C, Dussauge JP, Babinsky H, Barakos GN (2011) Unsteady effects of shock wave induced separation: 220 (Notes on numerical fluid mechanics and multidisciplinary design), 1st edn. Springer
Edney B (1968) Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock. Technical report, Aeronautical Research Institute Sweden
Fiévet R, Koo H, Raman V, Auslender AH (2017) Numerical investigation of shock-train response to inflow boundary-layer variations. AIAA J 55(9):2888–2900
Hellsten A (2005) New advanced k-omega turbulence model for high-lift aerodynamics. AIAA J 43(9):1857–1869
Jarrin N, Benhamadouche S, Laurence D, Prosser R (2006) A synthetic-eddy-method for generating inflow conditions for large-eddy simulations. Int J Heat Fluid Flow 27(4):585–593
Klomparens R, Driscoll J, Gamba M (2015) Unsteadiness characteristics and pressure distribution of an oblique shock train. In: 53rd AIAA aerospace sciences meeting
Osher S, Chakravarthy S (1983) Upwind schemes and boundary conditions with applications to Euler equations in general geometries. J Comput Phys 50(3):447–481
Steijl R, Barakos GN (2008) Sliding mesh algorithm for CFD analysis of helicopter rotor-fuselage aerodynamics. Int J Numer Methods Fluids 58(5):527–549
Steijl R, Barakos GN, Badcock K (2006) A framework for CFD analysis of helicopter rotors in hover and forward flight. Int J Numer Methods Fluids 51(8):819–847
Sun LQ, Sugiyama H, Mizobata K, Hiroshima T, Tojo A (2005) Numerical and experimental study of the Mach 2 pseudo-shock wave in a supersonic duct
van Albada GD, van Leer B, Roberts WW (1982) A comparative study of computational methods in cosmic gas dynamics. Astron Astrophys 108(1):76–84
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
Wallin S, Johansson AV (2000) An explicit algebraic Reynolds stress model for incompressible and compressible turbulent flows. J Fluid Mech 403:89–132
Author information
Authors and Affiliations
Corresponding author
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2022 The Author(s), under exclusive license to Springer Nature Switzerland AG
About this chapter
Cite this chapter
Boychev, K., Barakos, G.N., Steijl, R. (2022). Simulations of Multiple Shock Wave Boundary Layer Interactions with a Non-linear Turbulence Model. In: Knoerzer, D., Periaux, J., Tuovinen, T. (eds) Advances in Computational Methods and Technologies in Aeronautics and Industry. Computational Methods in Applied Sciences, vol 57. Springer, Cham. https://doi.org/10.1007/978-3-031-12019-0_5
Download citation
DOI: https://doi.org/10.1007/978-3-031-12019-0_5
Published:
Publisher Name: Springer, Cham
Print ISBN: 978-3-031-12018-3
Online ISBN: 978-3-031-12019-0
eBook Packages: Mathematics and StatisticsMathematics and Statistics (R0)