Numerical investigation on intake and wing
JAXA Supercomputer System Annual Report February 2022-January 2023
Report Number: R22ETET10
Subject Category: Skills Acquisition System
- Responsible Representative: Atsushi Hashimoto, Aviation Technology Directorate, Aircraft Lifecycle Innovation Hub
- Contact Information: Manami Fujii(m-fujii@moegi.waseda.jp)
- Members: Manami Fujii, Kohei Konishi, Keita Ogura, Kosuke Uchida
Abstract
JAXA and universities are advancing research to realize a hypersonic passenger airplane. This plan is divided into 4 stages and the 1st stage is called High-Mach Integrated Control Experiment, HIMICO. This is a hypersonic flight experiment aiming at establishing the integrated control technologies of the airframe and the engine. The performance of the supersonic intake is enhanced by increasing the intake back pressure. However, the excessively high back pressure is known to induce a buzz, which is a self-excited oscillation of the shock wave. The buzz causes a severe pressure vibration inside the engine and can result in the structural damage. Therefore, estimating the pressure waveform of the buzz and designing the engine which is resistant to the buzz is necessary. In this study, the numerical simulations were conducted aiming at clarifying the buzz mechanism and constructing the buzz model.
We also considered aerodynamics around lower speed aircraft. In recent years, CFD analysis has been used in aircraft development in earnest for aerodynamic design, and CFD has moved from the stage where it was primarily applied to design under cruise conditions to the complex high-lift configuration during takeoff and landing. CFD analysis of high-lift forms involves large scale separation, which makes it very difficult to accurately capture the flow field and make accurate predictions. Therefore, this study aims to improve the accuracy of stall prediction by evaluating the flow field in high-lift configuration using RANS method.
Reference URL
N/A
Reasons and benefits of using JAXA Supercomputer System
The flow of the supersonic intake and high lift devices are very complex that the calculation cost is large. However, the execution of the steady and unsteady simulations of the interested flow field became possible by using JSS3.
Achievements of the Year
The numerical simulations were conducted on the buzz occurring in the ramjet intake for HIMICO with several exit nozzle opening ratio (NOR). The time variations of the intake back pressure gained by CFD are shown in Fig. 1. During the pressure increasing period, the static pressure inside the intake increases because the inflow rate exceeds the outflow rate. As shown in Fig. 1, the pressure increasing period is divided into the two periods, pressure increasing period A and B. As a result of CFD, the intake back pressure increased more rapidly with the smaller NOR during the pressure increasing period B. The reason seems to be the smaller outflow rate with the smaller NOR. On the other hand, the intake back pressure of the increasing period A was found to be unaffected by the value of NOR although the outflow rate was influenced by the value of NOR. Therefore, the pressure increasing period A and B were suggested to be governed by the different mechanisms.
Some numerical simulations based on the workshops organized by AIAA ( Stability and Control prediction workshop and HiLift prediction workshop ) were carried out to improve the pitching moment prediction and the stall prediction in high lift configuration.
We found that a separation bubble appears at the juncture of the fuselage and the horizontal tail when using the isotropic turbulence models and the specific computational grids, suggested that this separation bubble strongly affects the pitching moment prediction.
RANS analysis was performed on the CRM-HL to validate the turbulence models on the stall prediction. The results showed that there were differences in the prediction of stall characteristics between the turbulence models at the high angle of attack.

Fig.2: The surface flow on the horizontal tail and the pitching moment coefficient on each computational grid
Publications
– Peer-reviewed papers
Manami Fujii, Shogo Ogura, Tetsuya Sato, Hideyuki Taguchi, Atsushi Hashimoto, Takashi Takahashi, “Effect of angle of attack on the performance of the supersonic intake for High Mach Integrated Control Experiment (HIMICO),” Aerospace Science and Technology, Vol. 127, No. 107687, 2022.
– Oral Presentations
1) Manami Fujii, Yusuke Hoshiya, Yuki Fujimori, Yuki Kuwabara, Rintaro Tanaka, Shima Ariyoshi, Ayuto Suzuki, Tetsuya Sato, Hideyuki Taguchi, Atsushi Hashimoto, “Numerical Investigation on the Effects of the Exit Nozzle Throat Height on the Buzz Characteristics Occurring in the Hypersonic Intake for High Mach Integrated Control Experiment (HIMICO),” Asian Joint Conference on Propulsion and Power 2023, AJCPP2023-105, Kanazawa, Mar. 2023.
2) Manami Fujii, Yusuke Hoshiya, Yuki Fujimori, Yuki Kuwabara, Rintaro Tanaka, Tetsuya Sato, Atsushi Hashimoto, Hideyuki Taguchi, “Numerical Investigation on the Buzz Phenomenon Occurring on the Ramjet Intake for High Mach Integrated Control Experiment (HIMICO),” The 54th Fluid Dynamics Conference/ The 40th Aerospace Numerical Simulation Symposium,1D12, Morioka, Jun. 2023.
3) Konishi, K., Kojima, Y., Hashimoto, A. and Kameda, M. (2023) “Prediction accuracy of RANS-based analysis for aerodynamic forces and moments of a civil aircraft model,” AIAA Scitech 2023 Forum (26 January 2023, National Harbor, MD, U.S.A.), AIAA 2023-1758.
4) Konishi, K., Kojima, Y., Hashimoto, A. and Kameda , M. (2022) “Prediction accuracy of RANS-based analysis for aerodynamic forces and moments of a civil aircraft model,” 54th Fluid Dynamics Conference / 40th Aerospace Numerical Simulation Symposium, Morioka, Iwate, Japan, 2A06.
Usage of JSS
Computational Information
- Process Parallelization Methods: MPI
- Thread Parallelization Methods: N/A
- Number of Processes: 576 – 4608
- Elapsed Time per Case: 30 Hour(s)
JSS3 Resources Used
Fraction of Usage in Total Resources*1(%): 0.93
Details
Please refer to System Configuration of JSS3 for the system configuration and major specifications of JSS3.
System Name | CPU Resources Used(Core x Hours) | Fraction of Usage*2(%) |
---|---|---|
TOKI-SORA | 23351080.01 | 1.02 |
TOKI-ST | 345176.59 | 0.34 |
TOKI-GP | 0.00 | 0.00 |
TOKI-XM | 598.35 | 0.37 |
TOKI-LM | 6922.14 | 0.46 |
TOKI-TST | 0.00 | 0.00 |
TOKI-TGP | 0.00 | 0.00 |
TOKI-TLM | 0.00 | 0.00 |
File System Name | Storage Assigned(GiB) | Fraction of Usage*2(%) |
---|---|---|
/home | 916.67 | 0.83 |
/data and /data2 | 55960.00 | 0.43 |
/ssd | 6876.67 | 0.95 |
Archiver Name | Storage Used(TiB) | Fraction of Usage*2(%) |
---|---|---|
J-SPACE | 0.08 | 0.00 |
*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.
ISV Software Licenses Used
ISV Software Licenses Used(Hours) | Fraction of Usage*2(%) | |
---|---|---|
ISV Software Licenses(Total) | 4867.61 | 3.39 |
*2: Fraction of Usage:Percentage of usage relative to each resource used in one year.
JAXA Supercomputer System Annual Report February 2022-January 2023