One-equation turbulence models applied to practical scramjet inlet
-
Amjad A. Pasha
,
Khalid A. Juhany
Abstract
Reynolds-averaged Navier–Stokes equations are used to simulate a practical scramjet inlet geometry using the shock-unsteadiness modified Spalart–Allmaras (SA) turbulence model. The geometry consists of fore-body ramps, expansion corners, and inlet ducts. The focus is to study the impingement of the cowl shock on the opposite wall boundary-layer. The resulting separation bubble can lead to blockage and inlet unstarts. The shock-unsteadiness correction is employed and is found to improve the computational fluid dynamics (CFD) prediction of flow separation in shock/boundary-layer interactions. The shock-unsteadiness parameter is calibrated against available experimental data of canonical flows, and the predicted flow-field is analyzed in detail. A large separation bubble size normalized to the upstream boundary-layer thickness of 4.6 is observed in the interaction region. Across the reattachment region in the interaction region, a peak value of wall pressure is observed. The inlet performance parameters are also calculated. The total pressure losses of 62% are observed across different shock waves, with an additional loss of 15% due to viscous boundary-layer effects.
Award Identifier / Grant number: G-503-135-1442
Acknowledgments
The authors acknowledge with thanks to the Deanship of Scientific Research (DSR) for technical and financial support. We would like to thank the high-performance centre (HPC) staff for providing us the Aziz supercomputing facility (http.//hpc.kau.edu.sa) to perform the numerical simulations. The authors would like to thank Prof. Krishnendu Sinha from the Department of Aerospace Engineering, Indian Institute of Technology Bombay, for his valuable guidance, help, and selflessness time investment to accomplish this work. The authors would also like to thank Mr. C. Vadivelan for his valuable support in this work.
-
Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
-
Research funding: This Project was funded by the Deanship of Scientific Research (DSR) at King Abdulaziz University, Jeddah, under grant no. G-503-135-1442.
-
Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Bose, D, Brown, JL, Prabhu, DK, Gnoffo, P, Johnston, CO, Hollis, B. Uncertainty assessment of hypersonic aerothermodynamics prediction capability. J Spacecraft Rockets 2013;50:12–8. https://doi.org/10.2514/1.a32268.Search in Google Scholar
2. Knight, D, Yan, H, Panaras, AG, Zheltovodov, A. Advances in CFD prediction of shock wave turbulent boundary layer interactions. Prog Aero Sci 2003;39:121–84. https://doi.org/10.1016/s0376-0421(02)00069-6.Search in Google Scholar
3. Zhiyin, Y. Large-eddy simulation: past, present and the future. Chin J Aeronaut 2015;28:11–24. https://doi.org/10.1016/j.cja.2014.12.007.Search in Google Scholar
4. Roy, CJ, Blottner, FG. Review and assessment of turbulence models for hypersonic flows. Prog Aero Sci 2007;42:469–530. https://doi.org/10.1016/j.paerosci.2006.12.002.Search in Google Scholar
5. Marvin, JG, Brown, JL, Gnoffo, PA. Experimental database with baseline CFD solutions: 2-D and axisymmetric hypersonic shock-wave/turbulent-boundary-layer interactions (NASA TM-2013-216604). Moffett Field , CA: NASA Ames Research Center; 2013.Search in Google Scholar
6. Sinha, K, Mahesh, K, Candler, GV. Modeling shock unsteadiness in shock/turbulence interaction. Phys Fluids 2003;15:2290–97. https://doi.org/10.1063/1.1588306.Search in Google Scholar
7. Sinha, K, Mahesh, K, Candler, GV. Modeling the effect of shock unsteadiness in shock/turbulent boundary-layer interactions. AIAA J 2005;43:586–94. https://doi.org/10.2514/1.8611.Search in Google Scholar
8. Pasha, AA, Juhany, KA. Numerical simulation of compression corner flows at Mach number 9. Chin J Aeronaut 2020;33:1611–24.10.1016/j.cja.2020.01.005Search in Google Scholar
9. Pasha, AA, Sinha, K. Shock-unsteadiness model applied to oblique shock wave/turbulent boundary-layer interaction. Int J Comput Fluid Dynam 2008;22:569–82. https://doi.org/10.1080/10618560802290284.Search in Google Scholar
10. Pasha, AA. Three-dimensional modeling shock-wave interaction with a fin at Mach 5. Arabian J Sci Eng 2018;43:4879–88. https://doi.org/10.1007/s13369-018-3210-6.Search in Google Scholar
11. Pasha, AA, Sinha, K. Simulation of hypersonic shock/turbulent boundary-layer interactions using shock-unsteadiness model. J Propul Power 2012;28:46–60. https://doi.org/10.2514/1.b34191.Search in Google Scholar
12. Pasha, AA. Study of parameters affecting separation bubble size in high speed flows using K-ω turbulence model. J Appl Comput Mech 2018;4:95–104. https://doi.org/10.22055/jacm.2017.22761.1140.Search in Google Scholar
13. Ji, Z, Zhang, H, Wang, B. Thrust control strategy based on the minimum combustor inlet Mach number to enhance the overall performance of a scramjet engine. Proc IME G J Aero Eng 2019;233:4810–24. https://doi.org/10.1177/0954410019830816.Search in Google Scholar
14. Curran, ET, Murthy, SNB. Scramjet propulsion, progress in astronautics and aeronautics. AIAA 2000;189:539–49.10.2514/4.866609Search in Google Scholar
15. Wilcox, DC. Turbulence modeling for CFD, 2nd ed. La Cañada, CA: DCW Industries; 2000.Search in Google Scholar
16. Spalart, P, Allmaras, S. A one-equation turbulence model for aerodynamic flows. In: 30th aerospace sciences meeting and exhibit. Reston, Virginia: American Institute of Aeronautics and Astronautics; 1992.10.2514/6.1992-439Search in Google Scholar
17. MacCormack, RW, Candler, GV. The solution of the Navier-Stokes equations using Gauss-Seidel line relaxation. Comput Fluid 1989;17:135–50. https://doi.org/10.1016/0045-7930(89)90012-1.Search in Google Scholar
18. Wright, MJ, Bose, D, Candler, GV. Data-parallel line relaxation method for the Navier-Stokes equations. AIAA J 1998;36:1603–9. https://doi.org/10.2514/2.586.Search in Google Scholar
19. Sinha, K, Candler, G. Convergence improvement of two-equation turbulence model calculations (Paper no. AIAA-Paper-1998-2649). In: 29th AIAA fluid dynamics conference. Albuquerque, NM: AIAA; 1998.10.2514/6.1998-2649Search in Google Scholar
20. Ali Pasha, A, Juhany, KA, Khalid, M. Numerical prediction of shock/boundary-layer interactions at high Mach numbers using a modified Spalart--Allmaras model. Eng Appl Comput Fluid Mech 2018;12:459–72. https://doi.org/10.1080/19942060.2018.1451389.Search in Google Scholar
21. Schülein, E. Skin friction and heat flux measurements in shock/boundary layer interaction flows. AIAA J 2006;44:1732–41. https://doi.org/10.2514/1.15110.Search in Google Scholar
22. Gaitonde, DV. Progress in shock wave/boundary layer interactions. Prog Aero Sci 2015;72:80–99. https://doi.org/10.1016/j.paerosci.2014.09.002.Search in Google Scholar
23. Edney, BE. Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock. Stockholm: The Aeronautical Research Institute of Sweden; 1968, FFA Rept. 115.10.2172/4480948Search in Google Scholar
24. Anderson, JD. Modern compressible flow with historical perspective, 3rd ed. New York: McGraw-Hill Book Co; 2002.Search in Google Scholar
25. Arnal, D, Délery, J. Laminar-turbulent transition and shock wave/boundary-layer interaction (RTO-EN-AVT-116, Chapter 4); 2004:1–46 pp. Available from: https://pdfs.semanticscho lar.org/3224/0f5392b502c1541e95f6bdf451fcac5daee2.pdf.Search in Google Scholar
© 2021 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Investigations of Trenched Film Hole Orientation Angle on Film Cooling Effectiveness
- Jet Flow Control Using Semi-Circular Corrugated Tab
- Simulation of Use-Related Multi-Parameter Load Spectrum Based on Principal Component Analysis
- Characterization of Tandem Airfoil Configurations of Axial Compressors
- Research on Suppressing Vibration of Mistuning Cyclic-Periodic Structure
- Research on Power Regulation Schedule Control System for Turboprop Engine
- Enhancement of Full Coverage Film Cooling Effectiveness with Mixed Injection Holes
- CFD Analysis and Experimental Validation of the Flow Field in a Rib Roughed Turbine Internal Cooling Channel
- Perforated Wall in Controlling the Separation Bubble Due to Shock Wave –Boundary Layer Interaction
- Calculating Endogenous and Exogenous Exergy Destruction for an Experimental Turbojet Engine
- One-equation turbulence models applied to practical scramjet inlet
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Investigations of Trenched Film Hole Orientation Angle on Film Cooling Effectiveness
- Jet Flow Control Using Semi-Circular Corrugated Tab
- Simulation of Use-Related Multi-Parameter Load Spectrum Based on Principal Component Analysis
- Characterization of Tandem Airfoil Configurations of Axial Compressors
- Research on Suppressing Vibration of Mistuning Cyclic-Periodic Structure
- Research on Power Regulation Schedule Control System for Turboprop Engine
- Enhancement of Full Coverage Film Cooling Effectiveness with Mixed Injection Holes
- CFD Analysis and Experimental Validation of the Flow Field in a Rib Roughed Turbine Internal Cooling Channel
- Perforated Wall in Controlling the Separation Bubble Due to Shock Wave –Boundary Layer Interaction
- Calculating Endogenous and Exogenous Exergy Destruction for an Experimental Turbojet Engine
- One-equation turbulence models applied to practical scramjet inlet
