Effect of flow compressibility in convergent-divergent nozzle
: Nozzles come in a range of shapes and sizes based on a purpose such as De Laval nozzle also known as the converging diverging nozzle. Convergent- divergent nozzle is commonly used in modern rocket engines that accelerates at high velocity till the supersonic region Ma>1. This paper aims t...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
FAZ Publishing
2022
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| Subjects: | |
| Online Access: | http://eprints.uthm.edu.my/8113/ http://eprints.uthm.edu.my/8113/1/J14839_3ac193fad75e6aa907bc4750adf5f72b.pdf |
| _version_ | 1848889303509237760 |
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| author | Hakimi, Muhammad Adib Nordin, Normayati |
| author_facet | Hakimi, Muhammad Adib Nordin, Normayati |
| author_sort | Hakimi, Muhammad Adib |
| building | UTHM Institutional Repository |
| collection | Online Access |
| description | : Nozzles come in a range of shapes and sizes based on a purpose such as De Laval nozzle
also known as the converging diverging nozzle. Convergent- divergent nozzle is commonly used in
modern rocket engines that accelerates at high velocity till the supersonic region Ma>1. This paper
aims to investigate numerically the effect of area ratio of the convergent divergent throat and the
Mach number from the incompressible flow to compressible flow. The software that were used to
simulate cases is ANSYS Computational Fluid Dynamics (CFD) code FLUENT. The area ratio
throat (AR= 5mm, 6mm, 7mm, and 8mm) and Mach number (Ma = 0.2, 1.0 and 1.8) was varied to
obtain more specific result. The result from this paper has shown that the most effective Mach
number and area ratio are at the 0.2 Ma with the AR=5mm According to the findings of this research,
the most effective Mach number and area ratio are at 0.2 Ma with AR=5mm. According to the
calculations performed in this research, the percentage variation of velocity at 0.2Ma was larger
than at 1.0 Ma and 1.8 Ma. This happen cause at the sonic and supersonic flow there is factor that
disturb the flow such as the back pressure and normal shock |
| first_indexed | 2025-11-15T20:24:02Z |
| format | Article |
| id | uthm-8113 |
| institution | Universiti Tun Hussein Onn Malaysia |
| institution_category | Local University |
| language | English |
| last_indexed | 2025-11-15T20:24:02Z |
| publishDate | 2022 |
| publisher | FAZ Publishing |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | uthm-81132022-12-18T02:59:19Z http://eprints.uthm.edu.my/8113/ Effect of flow compressibility in convergent-divergent nozzle Hakimi, Muhammad Adib Nordin, Normayati T Technology (General) : Nozzles come in a range of shapes and sizes based on a purpose such as De Laval nozzle also known as the converging diverging nozzle. Convergent- divergent nozzle is commonly used in modern rocket engines that accelerates at high velocity till the supersonic region Ma>1. This paper aims to investigate numerically the effect of area ratio of the convergent divergent throat and the Mach number from the incompressible flow to compressible flow. The software that were used to simulate cases is ANSYS Computational Fluid Dynamics (CFD) code FLUENT. The area ratio throat (AR= 5mm, 6mm, 7mm, and 8mm) and Mach number (Ma = 0.2, 1.0 and 1.8) was varied to obtain more specific result. The result from this paper has shown that the most effective Mach number and area ratio are at the 0.2 Ma with the AR=5mm According to the findings of this research, the most effective Mach number and area ratio are at 0.2 Ma with AR=5mm. According to the calculations performed in this research, the percentage variation of velocity at 0.2Ma was larger than at 1.0 Ma and 1.8 Ma. This happen cause at the sonic and supersonic flow there is factor that disturb the flow such as the back pressure and normal shock FAZ Publishing 2022 Article PeerReviewed text en http://eprints.uthm.edu.my/8113/1/J14839_3ac193fad75e6aa907bc4750adf5f72b.pdf Hakimi, Muhammad Adib and Nordin, Normayati (2022) Effect of flow compressibility in convergent-divergent nozzle. Journal of Complex Flow, 4 (2). pp. 33-38. ISSN 2672-7374 |
| spellingShingle | T Technology (General) Hakimi, Muhammad Adib Nordin, Normayati Effect of flow compressibility in convergent-divergent nozzle |
| title | Effect of flow compressibility in convergent-divergent nozzle |
| title_full | Effect of flow compressibility in convergent-divergent nozzle |
| title_fullStr | Effect of flow compressibility in convergent-divergent nozzle |
| title_full_unstemmed | Effect of flow compressibility in convergent-divergent nozzle |
| title_short | Effect of flow compressibility in convergent-divergent nozzle |
| title_sort | effect of flow compressibility in convergent-divergent nozzle |
| topic | T Technology (General) |
| url | http://eprints.uthm.edu.my/8113/ http://eprints.uthm.edu.my/8113/1/J14839_3ac193fad75e6aa907bc4750adf5f72b.pdf |