Flow Characteristics of a Mixed Compression Hypersonic Intake

Document Type : Regular Article

Authors

Department of Mechanical Engineering, Andong National University, Andong,36729, Republic of Korea

Abstract

The flow field in a two-dimensional hypersonic mixed-compression inlet in a freestream Mach numbers of M∞ =2.0, 3.0, and 5.0 are numerically solved to understand the effect of throat area variation. The exit area ratio variation is simulated by placing a plug insert at different axial locations at the exit of the model. The flow field is achieved computationally by solving the Reynolds Averaged Navier-Stokes equations in a finite volume framework. For each flow condition, the variation in shock structure is analyzed and the variation of the oblique shock wave angle with the mass flow rate is calculated theoretically and compared with the present CFD analysis. The variation in oblique shock angle is calculated in terms of the mass flow rate by considering the capture area and spillage flow through the inlet. The theoretical results suggest that the method can predict the inlet operating conditions at different freestream Mach numbers and area ratios. This method can quantify the reduction in mass flow rate due to the throttling effect by analyzing the flow field shock pattern. The effects of various important performance parameters such as free stream Mach number, total pressure recovery, and mass flow ratio were then numerically investigated. As the Mach number is increased, the total pressure recovery is reduced, but the maximum value of the mass flow rate is increased. The analysis is also focused on the effect of throat area variation on performance parameters at each Mach number. The characteristic curve of the inlet is then obtained for each free stream Mach number.

Keywords

References

Abedi, M., R. Askari and M. R. Soltani (2020). Numerical simulation of inlet buzz. Aerospace Science and Technology 97, 105547.##
Chang, J., W. Bao, Y. Fan and D. Yu (2009). Performance optimization of hypersonic inlets with pulse periodic energy addition. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 223(6), 691–699.##
Chen, X., C. Zhou, Y. Zheng and Y. Ju (2005a). Influence of cowl leading edge on inlet performance of ramjet assisted-range projectiles. 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 3642.##
Chen, X., Y. Zheng, C. Zhou and Y. Ju (2005b). Numerical simulation on ramjet inlet with different cowl leading edge. 35th AIAA Fluid Dynamics Conference and Exhibit, 5288.##
Clemens, N. T. and V. Narayanaswamy (2014). Low-Frequency Unsteadiness of Shock Wave/Turbulent Boundary Layer Interactions. Annual Review of Fluid Mechanics 46(September), 469–492.##
Curran, E. T. and S. N. B. Murthy (2001). Scramjet Propulsion. In S. N. B. Murthy and E. T. Curran (Eds.), AIAA. American Institute of Aeronautics and Astronautics.##
Das, S. and J. K. Prasad (2009). Cowl deflection angle in a supersonic air intake. Defence Science Journal 59(2), 99–105.##
Das, S. and J. K. Prasad (2010). Starting characteristics of a rectangular supersonic air-intake with cowl deflection. Aeronautical Journal 114(1153), 177–189.##
Fan, J. (2011). Optimal speed of hypersonic cruise flight. Theoretical and Applied Mechanics Letters 1(1), 012004.##
Gokhale, S. S. and V. R. Kumar (2001). Numerical computations of supersonic inlet flow. International Journal for Numerical Methods in Fluids 36(5), 597–617.##
James, K. J., A. Suryan and H. D. Kim (2021). Buzz characteristics and separation bubble dynamics in supersonic intake. Aerospace Science and Technology 115, 106795.##
Lee, J. and S. H. Kang (2019). Numerical study on the start and unstart phenomena in a scramjet inlet-isolator model. PLOS ONE, 14(11), e0224994.##
Li, N., J. T. Chang, K. J. Xu, D. R. Yu, W. Bao and Y. P. Song (2017). Prediction dynamic model of shock train with complex background waves. Physics of Fluids 29(11), 116103.##
Li, N., J. T. Chang, K. J. Xu, D. R. Yu, W. Bao and Y. P. Song (2018). Oscillation of the shock train in an isolator with incident shocks. Physics of Fluids 30(11), 116102.##
Liang, J. H., X.-Q. Fan, Y. Wang and W. D. Liu (2008). Performance enhancement of three-dimensional hypersonic inlet with sidewall compression. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 222(8), 1211–1219.##
Marguart, E. J. (1991). Predictions and measurements of internal and external flow fields of a generic hypersonic inlet. 9th Applied Aerodynamics Conference, 3320.##
Menter, F. (1993). Zonal Two Equation k-w Turbulence Models For Aerodynamic Flows. 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, 2906.##
Menter, F. R. (1994). Two-equation eddy-viscosity turbulence models for engineering applications. AIAA Journal 32(8), 1598–1605.##
Nair, M. T., N. Kumar and S. K. Saxena (2005). Computational analysis of inlet aerodynamics for a hypersonic research vehicle. Journal of Propulsion and Power 21(2), 286–291.##
Raj, N. O. P. and K. Venkatasubbaiah (2012). A new approach for the design of hypersonic scramjet inlets. Physics of Fluids 24(8), 086103.##
Ram, P., T. Kim and H. Kim (2020). Numerical study on shock train characteristics in divergent channels. Journal of Applied Fluid Mechanics 13(4), 1735–3645.##
Roy, C. J. and F. G. Blottner (2006). Review and assessment of turbulence models for hypersonic flows. Progress in Aerospace Sciences 42(7–8), 469–530.##
Soltani, M. R., J. S. Younsi, M. Farahani and A. Masoud (2013). Numerical simulation and parametric study of a supersonic intake. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 227(3), 467–479.##
Van Wie, D. M., F. T. Kwok and R. F. Walsh (1996). Starting characteristics of supersonic inlets. 32nd Joint Propulsion Conference and Exhibit, 2914.##
Wang, W. and R. Guo (2013). Numerical study of unsteady starting characteristics of a hypersonic inlet. Chinese Journal of Aeronautics 26(3), 563–571.##
Wang, Z., J. Chang, W. Hou and D. Yu (2020). Low-frequency unsteadiness of shock-wave/boundary-layer interaction in an isolator with background waves. Physics of Fluids 32(5), 056105.##
Weir, L., D. R. Reddy and G. Rupp (1989). Mach 5 inlet CFD and experimental results. 25th Joint Propulsion Conference, 2355.##
Xiang, G. X., C. Wang, H. H. Teng and Z. L. Jiang (2016). Investigations of Three-Dimensional Shock/Shock Interactions over Symmetrical Intersecting Wedges. AIAA Journal 54(5), 1472–1481.##
Xiang, G. X., X. Gao, W. J. Tang, X. Z. Jie and X. Huang (2020a). Numerical study on transition structures of oblique detonations with expansion wave from finite-length cowl. Physics of Fluids 32(5), 056108.##
Xiang, G., X. Gao, X. Jie, X. Li, H. Li and X. Chen (2020b). Flowfield characteristics in sidewall compression inlets. Acta Mechanica Sinica, 36(3), 678–685.##
Xiang, G., Y. Zhang, X. Gao, H. Li and X. Huang (2021). Oblique detonation waves induced by two symmetrical wedges in hydrogen-air mixtures. Fuel 295, 120615.##
Zha, G. C., D. Smith, M. Schwabacher, K. Rasheed, A. Gelsey, D. Knight and M. Haas (1997). High-performance supersonic missile inlet design using automated optimization. Journal of Aircraft 34(6), 697–705.##
Journal of Applied Fluid Mechanics
Volume 15, Issue 3 - Serial Number 64
May and June 2022
Pages 633-644

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History

  • Received: 13 August 2021
  • Revised: 09 December 2021
  • Accepted: 12 December 2021
  • Available online: 13 March 2022

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