LES of Supersonic Combustion in a Mach 2 Cavity-Based Model Scramjet Combustor with Conjugate Heat Transfer and Radiative Heat Transfer
(2025) AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025 In AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025- Abstract
Here we report on reactive Large Eddy Simulations (LES) of flow and combustion in the US Air Force Research Laboratory Research Cell 19 cavity-based scramjet combustor. This case involves combustion of ethylene (C2H4) injected into a cavity from its slanted trailing edge. It has previously been studied experimentally with multiple techniques including particle image velocimetry, shadowgrapy, OH planar laser-induced fluorescence, hyper-spectral imagining, laser induced breakdown spectroscopy, and quantified infrared radiation imaging as well as numerically using Finite Rate Chemistry (FRC) Reynolds Averaged Navier Stokes (RANS), hybrid RANS/LES and LES. Here, we expand on current knowledge by performing an investigation of flow and... (More)
Here we report on reactive Large Eddy Simulations (LES) of flow and combustion in the US Air Force Research Laboratory Research Cell 19 cavity-based scramjet combustor. This case involves combustion of ethylene (C2H4) injected into a cavity from its slanted trailing edge. It has previously been studied experimentally with multiple techniques including particle image velocimetry, shadowgrapy, OH planar laser-induced fluorescence, hyper-spectral imagining, laser induced breakdown spectroscopy, and quantified infrared radiation imaging as well as numerically using Finite Rate Chemistry (FRC) Reynolds Averaged Navier Stokes (RANS), hybrid RANS/LES and LES. Here, we expand on current knowledge by performing an investigation of flow and combustion using FRC-LES of two cases with fueling rates of 56 and 99 slpm, respectively. To improve the accuracy of the LES results the simulations reported include thermal radiation by means of the P1 spherical-harmonics method together with the weighted-sum-of-gray-gases model for the emissivity, and a conjugate heat transfer model to take the thermal wall conditions better into account. Comparisons are made with existing experimental data for a non-reacting case to establish the accuracy of the LES. For the reacting cases, comparisons are made with experimental data and previous FRC-LES without thermal radiation and conjugate heat transfer models to assess the influence the physics of thermal radiation and conjugate heat transfer. The LES results are further investigated in order to further develop our present understanding of cavity stabilized scramjet combustion.
(Less)
- author
- Fureby, C. LU
- organization
- publishing date
- 2025
- type
- Chapter in Book/Report/Conference proceeding
- publication status
- published
- subject
- host publication
- AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025
- series title
- AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025
- publisher
- American Institute of Aeronautics and Astronautics
- conference name
- AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025
- conference location
- Orlando, United States
- conference dates
- 2025-01-06 - 2025-01-10
- external identifiers
-
- scopus:85219502465
- ISBN
- 9781624107238
- DOI
- 10.2514/6.2025-0391
- language
- English
- LU publication?
- yes
- additional info
- Publisher Copyright: © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
- id
- 43504165-44c4-440c-b70d-5b82d18da016
- date added to LUP
- 2025-07-03 09:46:04
- date last changed
- 2025-07-03 09:46:45
@inproceedings{43504165-44c4-440c-b70d-5b82d18da016,
abstract = {{<p>Here we report on reactive Large Eddy Simulations (LES) of flow and combustion in the US Air Force Research Laboratory Research Cell 19 cavity-based scramjet combustor. This case involves combustion of ethylene (C2H4) injected into a cavity from its slanted trailing edge. It has previously been studied experimentally with multiple techniques including particle image velocimetry, shadowgrapy, OH planar laser-induced fluorescence, hyper-spectral imagining, laser induced breakdown spectroscopy, and quantified infrared radiation imaging as well as numerically using Finite Rate Chemistry (FRC) Reynolds Averaged Navier Stokes (RANS), hybrid RANS/LES and LES. Here, we expand on current knowledge by performing an investigation of flow and combustion using FRC-LES of two cases with fueling rates of 56 and 99 slpm, respectively. To improve the accuracy of the LES results the simulations reported include thermal radiation by means of the P1 spherical-harmonics method together with the weighted-sum-of-gray-gases model for the emissivity, and a conjugate heat transfer model to take the thermal wall conditions better into account. Comparisons are made with existing experimental data for a non-reacting case to establish the accuracy of the LES. For the reacting cases, comparisons are made with experimental data and previous FRC-LES without thermal radiation and conjugate heat transfer models to assess the influence the physics of thermal radiation and conjugate heat transfer. The LES results are further investigated in order to further develop our present understanding of cavity stabilized scramjet combustion.</p>}},
author = {{Fureby, C.}},
booktitle = {{AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025}},
isbn = {{9781624107238}},
language = {{eng}},
publisher = {{American Institute of Aeronautics and Astronautics}},
series = {{AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025}},
title = {{LES of Supersonic Combustion in a Mach 2 Cavity-Based Model Scramjet Combustor with Conjugate Heat Transfer and Radiative Heat Transfer}},
url = {{http://dx.doi.org/10.2514/6.2025-0391}},
doi = {{10.2514/6.2025-0391}},
year = {{2025}},
}