Numerical Analysis of Convergent-Divergent Angles and Operating Conditions Impact on Rocket Nozzle Performance Parameters
Comprehensive numerical analysis was conducted to elucidate the exhaust performance of rocket engine nozzles. The study focused on unravelling the intricate relationship between convergence and divergence angles and their impact on the exhaust performance parameters, including velocity coefficient (...
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| Format: | Article |
| Language: | English |
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National Institute for Aerospace Research “Elie Carafoli” - INCAS
2024-03-01
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| Series: | INCAS Bulletin |
| Subjects: | |
| Online Access: | https://bulletin.incas.ro/files/alili_kaddouri_mokadem_alami__vol_16_iss_1.pdf |
| _version_ | 1797263337987244032 |
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| author | Nabila ALILI Khacem KADDOURI Salem MOKADEM Ahmed ALAMI |
| author_facet | Nabila ALILI Khacem KADDOURI Salem MOKADEM Ahmed ALAMI |
| author_sort | Nabila ALILI |
| collection | DOAJ |
| description | Comprehensive numerical analysis was conducted to elucidate the exhaust performance of rocket engine nozzles. The study focused on unravelling the intricate relationship between convergence and divergence angles and their impact on the exhaust performance parameters, including velocity coefficient (cv), angularity coefficient (Ca), and gross thrust coefficient (Cfg). In contrast to conventional studies that focus mainly on the divergent section, this research delved into both convergent and divergent aspects of nozzle geometry. For the convergent section, a range of angles from 20° to 45° was systematically examined. For the divergent section, a wide spectrum of angles was explored, ranging from small (10°-13°), medium (14°-19°) and large (20°-25°) divergent angles. Further, we venture beyond geometry, investigating the influence of nozzle pressure ratio (NPR) on these key metrics. Realisable 𝑘𝑘−𝜀𝜀, enhanced wall traitement was used to simulate nozzle flow. The study identified the optimal convergent angle at 37.5°. The 15° diverging angle provides good overall performance, while the 23° angle strikes the ideal compromise: maximizing thrust and efficiency while minimizing weight and maintaining optimal performance. |
| first_indexed | 2024-04-25T00:11:25Z |
| format | Article |
| id | doaj.art-8c5f48eef2ee4919868a4f48131da5ec |
| institution | Directory Open Access Journal |
| issn | 2066-8201 2247-4528 |
| language | English |
| last_indexed | 2024-04-25T00:11:25Z |
| publishDate | 2024-03-01 |
| publisher | National Institute for Aerospace Research “Elie Carafoli” - INCAS |
| record_format | Article |
| series | INCAS Bulletin |
| spelling | doaj.art-8c5f48eef2ee4919868a4f48131da5ec2024-03-13T11:55:09ZengNational Institute for Aerospace Research “Elie Carafoli” - INCASINCAS Bulletin2066-82012247-45282024-03-0116131410.13111/2066-8201.2024.16.1.1Numerical Analysis of Convergent-Divergent Angles and Operating Conditions Impact on Rocket Nozzle Performance ParametersNabila ALILI0Khacem KADDOURI1Salem MOKADEM2Ahmed ALAMI3Laboratory of Physical Mechanics of Materials (LMPM), Mechanical Engineering Department, Djillali Liabes University, City Larbi Ben Mhidi, P.O. Box 89, 22000 Sidi Bel Abbes, Algeria, alili.16nabila@gmail.com*, nabila.alili@univ-sba.dzLaboratory of Physical Mechanics of Materials (LMPM), Mechanical Engineering Department, Djillali Liabes University, City Larbi Ben Mhidi, P.O. Box 89, 22000 Sidi Bel Abbes, AlgeriaLaboratory of Physical Mechanics of Materials (LMPM), Mechanical Engineering Department, Djillali Liabes University, City Larbi Ben Mhidi, P.O. Box 89, 22000 Sidi Bel Abbes, AlgeriaLaboratory of Process Engineering, Materials and Environment, Sidi Bel Abbes, AlgeriaComprehensive numerical analysis was conducted to elucidate the exhaust performance of rocket engine nozzles. The study focused on unravelling the intricate relationship between convergence and divergence angles and their impact on the exhaust performance parameters, including velocity coefficient (cv), angularity coefficient (Ca), and gross thrust coefficient (Cfg). In contrast to conventional studies that focus mainly on the divergent section, this research delved into both convergent and divergent aspects of nozzle geometry. For the convergent section, a range of angles from 20° to 45° was systematically examined. For the divergent section, a wide spectrum of angles was explored, ranging from small (10°-13°), medium (14°-19°) and large (20°-25°) divergent angles. Further, we venture beyond geometry, investigating the influence of nozzle pressure ratio (NPR) on these key metrics. Realisable 𝑘𝑘−𝜀𝜀, enhanced wall traitement was used to simulate nozzle flow. The study identified the optimal convergent angle at 37.5°. The 15° diverging angle provides good overall performance, while the 23° angle strikes the ideal compromise: maximizing thrust and efficiency while minimizing weight and maintaining optimal performance.https://bulletin.incas.ro/files/alili_kaddouri_mokadem_alami__vol_16_iss_1.pdfrocket engine nozzlek-epsilon turbulence modelconvergence angledivergence anglegross thrust coefficientvelocity coefficient |
| spellingShingle | Nabila ALILI Khacem KADDOURI Salem MOKADEM Ahmed ALAMI Numerical Analysis of Convergent-Divergent Angles and Operating Conditions Impact on Rocket Nozzle Performance Parameters INCAS Bulletin rocket engine nozzle k-epsilon turbulence model convergence angle divergence angle gross thrust coefficient velocity coefficient |
| title | Numerical Analysis of Convergent-Divergent Angles and Operating Conditions Impact on Rocket Nozzle Performance Parameters |
| title_full | Numerical Analysis of Convergent-Divergent Angles and Operating Conditions Impact on Rocket Nozzle Performance Parameters |
| title_fullStr | Numerical Analysis of Convergent-Divergent Angles and Operating Conditions Impact on Rocket Nozzle Performance Parameters |
| title_full_unstemmed | Numerical Analysis of Convergent-Divergent Angles and Operating Conditions Impact on Rocket Nozzle Performance Parameters |
| title_short | Numerical Analysis of Convergent-Divergent Angles and Operating Conditions Impact on Rocket Nozzle Performance Parameters |
| title_sort | numerical analysis of convergent divergent angles and operating conditions impact on rocket nozzle performance parameters |
| topic | rocket engine nozzle k-epsilon turbulence model convergence angle divergence angle gross thrust coefficient velocity coefficient |
| url | https://bulletin.incas.ro/files/alili_kaddouri_mokadem_alami__vol_16_iss_1.pdf |
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