Development and Application of a High-Speed Reacting Flow Solver in OpenFOAM

Authors

  • Sanjeev Adhikari Nanjing University of Aeronautics and Astronautics
  • Hao Tang Nanjing University of Aeronautics and Astronautics
  • Sudip Bhattrai Institute of Engineering, Tribhuvan University

DOI:

https://doi.org/10.3126/jiee.v5i1.41652

Keywords:

High-speed propulsion, Hypersonic flow, Oblique detonation waves, Shock-induced combustion

Abstract

A numerical study was conducted to verify and validate a new solver, named hyperReactingSodFoam, based on the OpenFOAM toolbox. This study mainly focuses on verification of solver’s computational capability to compute hypersonic flows involving shock-induced combustion, and its applications. This investigation is limited to inviscid flow and incorporates Minmod limiter to achieve total variation diminishing property. Analysis of a practical case was conducted by simulate and validate hypersonic blunt body projectile experiments at Mach 6.46 and 4.18. Likewise, to demonstrate the wider applicability of solver, a standing detonation in an oblique detonation wave engine combustor with a sharp as well as a blunted wedge geometry was studied. It was observed that, for a given flow condition and combustor geometry, a sharp wedge has a better mass-weighted average pressure recovery comparative to the blunted wedge. However, blunted wedge geometry provides a better picture of the detonation phenomenon as a practical wedge will have finite bluntness. In addition, the concept of the detonation induction length becomes less relevant for a blunted wedge.

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Published

2022-03-15

How to Cite

Adhikari, S., Tang, H., & Bhattrai, S. (2022). Development and Application of a High-Speed Reacting Flow Solver in OpenFOAM. Journal of Innovations in Engineering Education, 5(1), 15–24. https://doi.org/10.3126/jiee.v5i1.41652

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Articles