A Multifidelity Simulation Method for Internal and External Flow of a Hypersonic Airbreathing Propulsion System
As hypersonic vehicles are highly integrated, a multifidelity simulation method based on a commercial solver is developed to reduce simulation time for such vehicles and their propulsion systems. This method is characterized by high-level fidelity numerical analysis of external flow and low-level fi...
| Main Authors: | , , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
MDPI AG
2022-11-01
|
| Series: | Aerospace |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2226-4310/9/11/685 |
| _version_ | 1797469586362204160 |
|---|---|
| author | Jun Liu Huacheng Yuan Jinsheng Zhang Zheng Kuang |
| author_facet | Jun Liu Huacheng Yuan Jinsheng Zhang Zheng Kuang |
| author_sort | Jun Liu |
| collection | DOAJ |
| description | As hypersonic vehicles are highly integrated, a multifidelity simulation method based on a commercial solver is developed to reduce simulation time for such vehicles and their propulsion systems. This method is characterized by high-level fidelity numerical analysis of external flow and low-level fidelity numerical analysis of internal flow. The external flow of a propulsion system is solved by RANS equations. The internal flow is modeled by a quasi-one-dimensional equation. The interaction between external and internal flow is governed by a CFD solver through a user-defined function (UDF). The static pressure distribution acquired from the multifidelity simulation method is in agreement with the experimental data, indicating that this simulation method can be used to study the flow physics of hypersonic propulsion systems at a reasonable cost. From a design perspective, the results indicate that the horizontal force increases with the fuel equivalence ratio, and the thrust balance is realized at φ = 0.35. The positive net thrust is maintained throughout the flight regime from <i>Ma</i> 4 to <i>Ma</i> 7, whether the combustor operates in ramjet or scramjet mode. |
| first_indexed | 2024-03-09T19:22:28Z |
| format | Article |
| id | doaj.art-eaf5b8ad025d4027a9336d8b4d8d3ac0 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-09T19:22:28Z |
| publishDate | 2022-11-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-eaf5b8ad025d4027a9336d8b4d8d3ac02023-11-24T03:15:49ZengMDPI AGAerospace2226-43102022-11-0191168510.3390/aerospace9110685A Multifidelity Simulation Method for Internal and External Flow of a Hypersonic Airbreathing Propulsion SystemJun Liu0Huacheng Yuan1Jinsheng Zhang2Zheng Kuang3College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaCollege of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaCollege of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaCollege of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaAs hypersonic vehicles are highly integrated, a multifidelity simulation method based on a commercial solver is developed to reduce simulation time for such vehicles and their propulsion systems. This method is characterized by high-level fidelity numerical analysis of external flow and low-level fidelity numerical analysis of internal flow. The external flow of a propulsion system is solved by RANS equations. The internal flow is modeled by a quasi-one-dimensional equation. The interaction between external and internal flow is governed by a CFD solver through a user-defined function (UDF). The static pressure distribution acquired from the multifidelity simulation method is in agreement with the experimental data, indicating that this simulation method can be used to study the flow physics of hypersonic propulsion systems at a reasonable cost. From a design perspective, the results indicate that the horizontal force increases with the fuel equivalence ratio, and the thrust balance is realized at φ = 0.35. The positive net thrust is maintained throughout the flight regime from <i>Ma</i> 4 to <i>Ma</i> 7, whether the combustor operates in ramjet or scramjet mode.https://www.mdpi.com/2226-4310/9/11/685hypersonic airbreathing propulsion systemexternal and internal flowquasi-one-dimensional modelmultifidelity simulation method |
| spellingShingle | Jun Liu Huacheng Yuan Jinsheng Zhang Zheng Kuang A Multifidelity Simulation Method for Internal and External Flow of a Hypersonic Airbreathing Propulsion System Aerospace hypersonic airbreathing propulsion system external and internal flow quasi-one-dimensional model multifidelity simulation method |
| title | A Multifidelity Simulation Method for Internal and External Flow of a Hypersonic Airbreathing Propulsion System |
| title_full | A Multifidelity Simulation Method for Internal and External Flow of a Hypersonic Airbreathing Propulsion System |
| title_fullStr | A Multifidelity Simulation Method for Internal and External Flow of a Hypersonic Airbreathing Propulsion System |
| title_full_unstemmed | A Multifidelity Simulation Method for Internal and External Flow of a Hypersonic Airbreathing Propulsion System |
| title_short | A Multifidelity Simulation Method for Internal and External Flow of a Hypersonic Airbreathing Propulsion System |
| title_sort | multifidelity simulation method for internal and external flow of a hypersonic airbreathing propulsion system |
| topic | hypersonic airbreathing propulsion system external and internal flow quasi-one-dimensional model multifidelity simulation method |
| url | https://www.mdpi.com/2226-4310/9/11/685 |
| work_keys_str_mv | AT junliu amultifidelitysimulationmethodforinternalandexternalflowofahypersonicairbreathingpropulsionsystem AT huachengyuan amultifidelitysimulationmethodforinternalandexternalflowofahypersonicairbreathingpropulsionsystem AT jinshengzhang amultifidelitysimulationmethodforinternalandexternalflowofahypersonicairbreathingpropulsionsystem AT zhengkuang amultifidelitysimulationmethodforinternalandexternalflowofahypersonicairbreathingpropulsionsystem AT junliu multifidelitysimulationmethodforinternalandexternalflowofahypersonicairbreathingpropulsionsystem AT huachengyuan multifidelitysimulationmethodforinternalandexternalflowofahypersonicairbreathingpropulsionsystem AT jinshengzhang multifidelitysimulationmethodforinternalandexternalflowofahypersonicairbreathingpropulsionsystem AT zhengkuang multifidelitysimulationmethodforinternalandexternalflowofahypersonicairbreathingpropulsionsystem |