Fundamental Researches of Fluid and Combustion for the Hypersonic Flight
JAXA Supercomputer System Annual Report April 2019-March 2020
Report Number: R19ECMP18
Subject Category: Competitive Funding
- Responsible Representative: Kouichi Okita, Director, Research Unit IV, Research and Development Directorate
- Contact Information: Masahiro Takahashi(takahashi.masahiro@jaxa.jp)
- Members: Masahiro Takahashi, Masatoshi Kodera, Toshihiko Munakata, Masaaki Fukui, Masaharu Takahashi, Susumu Hasegawa, Sadatake Tomioka, Shun Takahashi
Abstract
The wind tunnel tests by using sub-scaled models play important roles for the development of the air-breathing propulsion system for a hypersonic transporter. However, in some cases, the flow of the wind tunnel is ”vitiated” due to the heating process and/or the complex flow-path of the facility. To rise the total temperature to produce the high Mach number flow, a combustion heating is usually applied, introducing the water vaper to the air stream. The complex flow-path of the facility would increase turbulence. Both the phenomena might affect the supersonic combustion process. To clarify the effects of the flow vitiation and ultimately, to establish the adjustment methodology that can deduce the data of real flight from the wind tunnel data, JAXA has initiated the 5-years study. The final goal is conducting the flight experiment to obtain the data on the supersonic combustion in an actual flight condition and verify the methodology.
Reference URL
N/A
Reasons and benefits of using JAXA Supercomputer System
Recently, hydrocarbon fuels become more promising fuels for a supersonic combustor than hydrogen because of those high thrust density. A gaseous ethylene is selected as the fuel for the present flight experiment. Ethylene is rather simple hydrocarbon, but much more chemical species contributes to the combustion process than hydrogen. In addition, the flow conditions in the supersonic combustor and those around the hypersonic flight test vehicle are quire severe. As a result, the CFD for the present design evaluation requires large computation time. Furthermore, many cases of the CFD must be executed for aerodynamic design of the flight test vehicle and the combustor model within the scheduled period. Therefore, the use of the JSS2 system is essential for the success of the present research program.
Achievements of the Year
(1) Flow-path design of a supersonic combustor for JAXA flight experiment
Flow-path design of a supersonic combustor for JAXA flight experiment was continued by using three-dimensional RANS simulation with a skeletal mechanism for ethylene-air combustion. Influence of the geometry of the flame-holding cavity and that of the fuel injection schemes on combustion were investigated numerically and some of the promising configurations have been selected. It is noted that, based on the CFD design study results, the combustor test models were manufactured and the combustion tests were conducted to fix the combustor configuration and fuel injection scheme. The whole combustor test model including an air capturing inlet was also manufactured and was tested in the Ramjet Engine Test Facility at JAXA Kakuda space center to confirm its operationality. Data accumulation for the CFD validation, including the measurements of the cross-sectional distribution of the combustion gas composition at the combustor exit, were also conducted, and the detailed CFD validation is undergoing.
(2) Development of a tool for predicting facility dependence on supersonic combustion
3D RANS simulation was continued to be carried out from last year to investigate the effect of water vapor in the air on scramjet combustion.
Various reduction mechanisms for ethylene / air combustion, which were generated from a detailed mechanism through the CHEMKIN-Pro / Reaction Workbench, were applied to 2D CFD for supersonic combustion flows, and the results were compared to the one with the detailed mechanism in order to verify the prediction ability.
(3) Evaluation of aerodynamic characteristics for JAXA flight experimental vehicle
Aerodynamic characteristics of JAXA flight experimental vehicle were predicted by using JAXA FaSTAR code for the flight Mach number range from 2 to 7 and the ranges of both the angle of attack and the yaw angle from 0 degree to 10 degree. Based on these aerodynamic characteristics data, the stability analysis and the trajectory calculation for the flight experimental vehicle were conducted. The inlet flow CFD was also conducted to obtain the flow condition at the combustor entrance, which is necessary for the combustor flow analysis.
(4) Development of a tool for predicting facility dependence on aerodynamic heating
A coupled analysis method of fluid dynamics and thermal heating is being developed to predict an effect of turbulence and combustion-heating of a test gas on the aerodynamic heating relating to duplication of flight condition in ground test facilities. The temperature distribution inside the object in a hypersonic non-equilibrium flow was investigated by the flow-thermal coupling analysis.
Publications
– Peer-reviewed papers
Takahashi, M., Tomioka, S., Kodera, M., Kobayashi, K., Hasegawa, S., Shimizu, T., Aono, J., Munakata, T., ”Numerical Study on Combustor Flow-Path Design for a Scramjet Flight Experiment,” Transactions of JSASS, Aerospace Technology Japan, 2020 (under peer-review).
– Non peer-reviewed papers
1) Takahashi, M., Tomioka, S., Kodera, M., Kobayashi, K., Hasegawa, S., Shimizu, T., Aono, J., Munakata, T., ”Numerical Study on Combustor Flow-Path Design for a Scramjet Flight Experiment,” Proceedings of 32nd International Symposium on Space Technology and Science and 9th Nano-Satellite Symposium, 2019.
2) Takahashi, M., Tomioka, S., ”Flow-path Design of a Combustor Model for a Supersonic-combustion Flight Experiment,” Proceedings of 51st Fluid Dynamics Conference / 37th Aerospace Numerical Simulation Symposium, 2019.
3) Takahashi, M., Kobayashi, K., Tomioka, S., ”Combustion Test Results of a Supersonic Combustor Model for a JAXA Flight Experiment,” Proceedings of FYR1 Space Transportation Symposium, 2020 (to be published).
4) Kodera, M., and Tomioka, S., “Investigation of Air Vitiation Effects on Scramjet Engine Performance,” Proceedings of 32nd International Symposium on Space Technology and Science and 9th Nano-Satellite Symposium, 2019.
5) Kobayashi, K., Tomioka, S., Takahashi, M., and Kodera, M., “Reaction Mechanism Reduction for Ethylene-Fueled Supersonic Combustion CFD,” Proceedings of 63rd Space Sciences and Technology Conference, 2019.
6) Hasegawa, S., Tani, K., Tomioka, S., ”Numerical Simulation of the Flow inside the Inlet for the Hypersonic Flight, ” Proceedings of 51st Fluid Dynamics Conference / 37th Aerospace Numerical Simulation Symposium, 2019.
7) Mizuno, Y., Takahashi, S., Yamada, G., Yamashita, R., ”Fluid-solid Thermal Coupling Simulation of Hypersonic Flow,” Proceedings of 51st Fluid Dynamics Conference / 37th Aerospace Numerical Simulation Symposium, 2019.
8) Mizuno, Y., Yamashita, R., Takahashi, S., Yamada, G., ”Accurate Prediction of the Aerodynamic Heating using Hypersonic Flow and Thermal Transfer Coupled Simulation,” Proceedings of 63rd Space Sciences and Technology Conference, 2019.
9) Mizuno, Y., Takahashi, S., Yamada, G., Yamashita, R., ”Investigation of Aerodynamic Heating under Hypersonic Flow using Coupled Flow – Thermal Analysis,” Proceedings of ASIA PACIFIC INTERNATIONAL SYMPOSIUM ON AEROSPACE TECHNOLOGY, 2019.
– Oral Presentations
1) Takahashi, M., Tomioka, S., Kodera, M., Kobayashi, K., Hasegawa, S., Shimizu, T., Aono, J., Munakata, T., ”Numerical Study on Combustor Flow-Path Design for a Scramjet Flight Experiment,” 32nd International Symposium on Space Technology and Science and 9th Nano-Satellite Symposium, 2019.
2) Takahashi, M., Tomioka, S., ”Flow-path Design of a Combustor Model for a Supersonic-combustion Flight Experiment,” 51st Fluid Dynamics Conference / 37th Aerospace Numerical Simulation Symposium, 2019.
3) Takahashi, M., Kobayashi, K., Tomioka, S., ”Combustion Test Results of a Supersonic Combustor Model for a JAXA Flight Experiment,” FYR1 Space Transportation Symposium, 2020.
4) Kodera, M., and Tomioka, S., “Investigation of Air Vitiation Effects on Scramjet Engine Performance,” 32nd International Symposium on Space Technology and Science and 9th Nano-Satellite Symposium, 2019.
5) Kobayashi, K., Tomioka, S., Takahashi, M., and Kodera, M., “Reaction Mechanism Reduction for Ethylene-Fueled Supersonic Combustion CFD,” 63rd Space Sciences and Technology Conference, 2019.
6) Hasegawa, S., Tani, K., Tomioka, S., ”Numerical Simulation of the Flow inside the Inlet for the Hypersonic Flight, ” 51st Fluid Dynamics Conference / 37th Aerospace Numerical Simulation Symposium, 2019.
7) Mizuno, Y., Takahashi, S., Yamada, G., Yamashita, R., ”’Fluid-solid Thermal Coupling Simulation of Hypersonic Flow,” 51st Fluid Dynamics Conference / 37th Aerospace Numerical Simulation Symposium, 2019.
8) Mizuno, Y., Yamashita, R., Takahashi, S., Yamada, G., ”Accurate Prediction of the Aerodynamic Heating using Hypersonic Flow and Thermal Transfer Coupled Simulation,” 63rd Space Sciences and Technology Conference, 2019.
9) Mizuno, Y., Takahashi, S., Yamada, G., Yamashita, R., ”Investigation of Aerodynamic Heating under Hypersonic Flow using Coupled Flow – Thermal Analysis,” ASIA PACIFIC INTERNATIONAL SYMPOSIUM ON AEROSPACE TECHNOLOGY, 2019.
Usage of JSS2
Computational Information
- Process Parallelization Methods: MPI
- Thread Parallelization Methods: OpenMP
- Number of Processes: 32 – 1920
- Elapsed Time per Case: 400 Hour(s)
Resources Used
Fraction of Usage in Total Resources*1(%): 1.89
Details
Please refer to System Configuration of JSS2 for the system configuration and major specifications of JSS2.
System Name | Amount of Core Time(core x hours) | Fraction of Usage*2(%) |
---|---|---|
SORA-MA | 17,100,809.54 | 2.08 |
SORA-PP | 6,134.46 | 0.04 |
SORA-LM | 11.77 | 0.00 |
SORA-TPP | 0.00 | 0.00 |
File System Name | Storage Assigned(GiB) | Fraction of Usage*2(%) |
---|---|---|
/home | 201.86 | 0.17 |
/data | 12,027.24 | 0.21 |
/ltmp | 3,304.04 | 0.28 |
Archiver Name | Storage Used(TiB) | Fraction of Usage*2(%) |
---|---|---|
J-SPACE | 7.40 | 0.19 |
*1: Fraction of Usage in Total Resources: Weighted average of three resource types (Computing, File System, and Archiver).
*2: Fraction of Usage:Percentage of usage relative to each resource used in one year.
JAXA Supercomputer System Annual Report April 2019-March 2020