Abstract
Two open-source solvers, Eilmer and hyFoam, are here considered for their performance in simulating high-speed flows in different flow conditions and geometric configurations typical of propulsive systems at supersonic speeds. The goal is to identify the open-source platform providing the best compromise between accuracy, flexibility and computational cost to eventually simulate the flow fields inside ramjet and scramjet engines. The differences in terms of discretization and solution methods of the selected solvers are discussed in terms of their impact on solution accuracy and computational efficiency and in view of the aerothermodynamic analysis and design of future trans-atmospheric propulsive systems. In this work steady state problems are considered. Numerical results of two scramjet type engines demonstrated a similar predictive capability of both codes in non-reacting conditions. These results highlight their potential to be considered for further characterization of overall engine performance.
| Language | English |
|---|---|
| Title of host publication | 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017 |
| Number of pages | 17 |
| DOIs | |
| Publication status | Published - 3 Apr 2017 |
| Event | 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017 - Xiamen, China Duration: 6 Mar 2017 → 9 Mar 2017 |
Conference
| Conference | 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017 |
|---|---|
| Country | China |
| City | Xiamen |
| Period | 6/03/17 → 9/03/17 |
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Keywords
- flow conditions
- propulsion systems
- ramjet engines
- scramjet engines
- Eilmer
- hyFoam
Cite this
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Numerical modeling and simulation of supersonic flows in propulsion systems by open-source solvers. / Hoste, Jimmy John O.E.; Casseau, Vincent; Fossati, Marco; Taylor, Ian J.; Gollan, Rowan J.
21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017. 2017. 2411.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
TY - GEN
T1 - Numerical modeling and simulation of supersonic flows in propulsion systems by open-source solvers
AU - Hoste, Jimmy John O.E.
AU - Casseau, Vincent
AU - Fossati, Marco
AU - Taylor, Ian J.
AU - Gollan, Rowan J.
PY - 2017/4/3
Y1 - 2017/4/3
N2 - Two open-source solvers, Eilmer and hyFoam, are here considered for their performance in simulating high-speed flows in different flow conditions and geometric configurations typical of propulsive systems at supersonic speeds. The goal is to identify the open-source platform providing the best compromise between accuracy, flexibility and computational cost to eventually simulate the flow fields inside ramjet and scramjet engines. The differences in terms of discretization and solution methods of the selected solvers are discussed in terms of their impact on solution accuracy and computational efficiency and in view of the aerothermodynamic analysis and design of future trans-atmospheric propulsive systems. In this work steady state problems are considered. Numerical results of two scramjet type engines demonstrated a similar predictive capability of both codes in non-reacting conditions. These results highlight their potential to be considered for further characterization of overall engine performance.
AB - Two open-source solvers, Eilmer and hyFoam, are here considered for their performance in simulating high-speed flows in different flow conditions and geometric configurations typical of propulsive systems at supersonic speeds. The goal is to identify the open-source platform providing the best compromise between accuracy, flexibility and computational cost to eventually simulate the flow fields inside ramjet and scramjet engines. The differences in terms of discretization and solution methods of the selected solvers are discussed in terms of their impact on solution accuracy and computational efficiency and in view of the aerothermodynamic analysis and design of future trans-atmospheric propulsive systems. In this work steady state problems are considered. Numerical results of two scramjet type engines demonstrated a similar predictive capability of both codes in non-reacting conditions. These results highlight their potential to be considered for further characterization of overall engine performance.
KW - flow conditions
KW - propulsion systems
KW - ramjet engines
KW - scramjet engines
KW - Eilmer
KW - hyFoam
U2 - 10.2514/6.2017-2411
DO - 10.2514/6.2017-2411
M3 - Conference contribution
SN - 9781624104633
BT - 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
ER -