Experimental and Numerical Study on the Vortical Flow of MULDICON Wing Configuration
This paper highlights the results and comparison of the flow topology investigation above the unmanned combat aerial vehicle (UCAV) configuration, namely, multidisciplinary design configuration (MULDICON), with modified leading-edge profile at the apex region from a sharp to a blunt profile to reduc...
Saved in:
| Main Authors: | , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
Wiley
2023-01-01
|
| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2023/4045164 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| _version_ | 1849685144982519808 |
|---|---|
| author | Ibrahim Madan Jiun-Jih Miau Shabudin Bin Mat |
| author_facet | Ibrahim Madan Jiun-Jih Miau Shabudin Bin Mat |
| author_sort | Ibrahim Madan |
| collection | DOAJ |
| description | This paper highlights the results and comparison of the flow topology investigation above the unmanned combat aerial vehicle (UCAV) configuration, namely, multidisciplinary design configuration (MULDICON), with modified leading-edge profile at the apex region from a sharp to a blunt profile to reduce the complexity of the flow structure above the wing. It was found from the flow visualization results that at a low angle of attack, for instance, 10°, the onset of the flow separation took place near the apex region; the onset of a tip vortex at the wing tip was also detected. At a medium angle of attack, for instance, 15°, the onset of the flow separation moved further upstream with the formation of the apex vortex, and the magnitude of the tip vortex increased due to increasing incoming flow with increasing the angle of attack. At higher angle of attack, for instance, 20°, the apex vortex intensity increased and wing tip vortices shedding is observed. Furthermore, at an angle of attack of 25°, the configuration is partially stalled, while a complete stalled occurred at an angle of attack of 30°. The current results obtained from this study have shown that the configuration has a maximum lift coefficient of 0.8 obtained from the K-Omega-SST turbulence model while it is 0.93 calculated from the Spalart-Allmaras turbulence model, while the maximum drag coefficient is 0.31 and 0.35, respectively, when calculated for the K-Omega-SST turbulence model and the Spalart-Allmaras turbulence model at an AOA of 25°. The flow visualization results revealed that there is a single flow separation due to modified leading edge from sharp to blunt, thus flow complexity is reduced. |
| format | Article |
| id | doaj-art-c3205d6bcb0446e3804c5639888dfd8b |
| institution | DOAJ |
| issn | 1687-5974 |
| language | English |
| publishDate | 2023-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-c3205d6bcb0446e3804c5639888dfd8b2025-08-20T03:23:15ZengWileyInternational Journal of Aerospace Engineering1687-59742023-01-01202310.1155/2023/4045164Experimental and Numerical Study on the Vortical Flow of MULDICON Wing ConfigurationIbrahim Madan0Jiun-Jih Miau1Shabudin Bin Mat2Department of Aeronautics and AstronauticsDepartment of Aeronautics and AstronauticsUTM AerolabThis paper highlights the results and comparison of the flow topology investigation above the unmanned combat aerial vehicle (UCAV) configuration, namely, multidisciplinary design configuration (MULDICON), with modified leading-edge profile at the apex region from a sharp to a blunt profile to reduce the complexity of the flow structure above the wing. It was found from the flow visualization results that at a low angle of attack, for instance, 10°, the onset of the flow separation took place near the apex region; the onset of a tip vortex at the wing tip was also detected. At a medium angle of attack, for instance, 15°, the onset of the flow separation moved further upstream with the formation of the apex vortex, and the magnitude of the tip vortex increased due to increasing incoming flow with increasing the angle of attack. At higher angle of attack, for instance, 20°, the apex vortex intensity increased and wing tip vortices shedding is observed. Furthermore, at an angle of attack of 25°, the configuration is partially stalled, while a complete stalled occurred at an angle of attack of 30°. The current results obtained from this study have shown that the configuration has a maximum lift coefficient of 0.8 obtained from the K-Omega-SST turbulence model while it is 0.93 calculated from the Spalart-Allmaras turbulence model, while the maximum drag coefficient is 0.31 and 0.35, respectively, when calculated for the K-Omega-SST turbulence model and the Spalart-Allmaras turbulence model at an AOA of 25°. The flow visualization results revealed that there is a single flow separation due to modified leading edge from sharp to blunt, thus flow complexity is reduced.http://dx.doi.org/10.1155/2023/4045164 |
| spellingShingle | Ibrahim Madan Jiun-Jih Miau Shabudin Bin Mat Experimental and Numerical Study on the Vortical Flow of MULDICON Wing Configuration International Journal of Aerospace Engineering |
| title | Experimental and Numerical Study on the Vortical Flow of MULDICON Wing Configuration |
| title_full | Experimental and Numerical Study on the Vortical Flow of MULDICON Wing Configuration |
| title_fullStr | Experimental and Numerical Study on the Vortical Flow of MULDICON Wing Configuration |
| title_full_unstemmed | Experimental and Numerical Study on the Vortical Flow of MULDICON Wing Configuration |
| title_short | Experimental and Numerical Study on the Vortical Flow of MULDICON Wing Configuration |
| title_sort | experimental and numerical study on the vortical flow of muldicon wing configuration |
| url | http://dx.doi.org/10.1155/2023/4045164 |
| work_keys_str_mv | AT ibrahimmadan experimentalandnumericalstudyonthevorticalflowofmuldiconwingconfiguration AT jiunjihmiau experimentalandnumericalstudyonthevorticalflowofmuldiconwingconfiguration AT shabudinbinmat experimentalandnumericalstudyonthevorticalflowofmuldiconwingconfiguration |