Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jets
Abstract Due to sever aerodynamic heating, the protection of forebody of scramjet is crucial for hypersonic flight. In present work, a new cooling system is proposed and investigated for the protection of nose cone at hypersonic flight. Computational fluid dynamic is used for the simulation of the l...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Nature Portfolio
2023-01-01
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| Series: | Scientific Reports |
| Online Access: | https://doi.org/10.1038/s41598-023-28127-9 |
| _version_ | 1828056948124155904 |
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| author | Reza Iranmanesh As’ad Alizadeh M. Faraji Gautam Choubey |
| author_facet | Reza Iranmanesh As’ad Alizadeh M. Faraji Gautam Choubey |
| author_sort | Reza Iranmanesh |
| collection | DOAJ |
| description | Abstract Due to sever aerodynamic heating, the protection of forebody of scramjet is crucial for hypersonic flight. In present work, a new cooling system is proposed and investigated for the protection of nose cone at hypersonic flight. Computational fluid dynamic is used for the simulation of the lateral and axial coolant jet released from the spike at high-velocity condition. The primary goal is to find optimum jet location for efficient cooling of nose and spike assembly. Influence of two coolant jets (Carbon dioxide and Helium) on the mechanism of cooling system are fully investigated. For simulation, RANS equations are coupled with species transport equation and SST turbulence model. Two different jet configurations (axial disk positions) are investigated to obtain efficient condition for protection of nose cone at hypersonic flight. Our results indicate that the presence of the spike on the nose cone decreases pressure up to 33% on the main body and the shifts the maximum pressure to higher angles because of the deflection of the air stream. Maximum pressure drops about 50% by injection of the coolant disk jet (C2) at angle of 55 deg. |
| first_indexed | 2024-04-10T21:03:31Z |
| format | Article |
| id | doaj.art-c2d1043d681449608d1c88f106d38cff |
| institution | Directory Open Access Journal |
| issn | 2045-2322 |
| language | English |
| last_indexed | 2024-04-10T21:03:31Z |
| publishDate | 2023-01-01 |
| publisher | Nature Portfolio |
| record_format | Article |
| series | Scientific Reports |
| spelling | doaj.art-c2d1043d681449608d1c88f106d38cff2023-01-22T12:11:31ZengNature PortfolioScientific Reports2045-23222023-01-011311910.1038/s41598-023-28127-9Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jetsReza Iranmanesh0As’ad Alizadeh1M. Faraji2Gautam Choubey3Faculty of Civil Engineering, K.N. Toosi University of TechnologyDepartment of Civil Engineering, College of Engineering, Cihan University-ErbilDepartment of Mechanical Engineering, Babol Noshirvani University of TechnologyDepartment of Mechanical & Aerospace Engineering, Institute of Infrastructure Technology Research and Management (IITRAM)Abstract Due to sever aerodynamic heating, the protection of forebody of scramjet is crucial for hypersonic flight. In present work, a new cooling system is proposed and investigated for the protection of nose cone at hypersonic flight. Computational fluid dynamic is used for the simulation of the lateral and axial coolant jet released from the spike at high-velocity condition. The primary goal is to find optimum jet location for efficient cooling of nose and spike assembly. Influence of two coolant jets (Carbon dioxide and Helium) on the mechanism of cooling system are fully investigated. For simulation, RANS equations are coupled with species transport equation and SST turbulence model. Two different jet configurations (axial disk positions) are investigated to obtain efficient condition for protection of nose cone at hypersonic flight. Our results indicate that the presence of the spike on the nose cone decreases pressure up to 33% on the main body and the shifts the maximum pressure to higher angles because of the deflection of the air stream. Maximum pressure drops about 50% by injection of the coolant disk jet (C2) at angle of 55 deg.https://doi.org/10.1038/s41598-023-28127-9 |
| spellingShingle | Reza Iranmanesh As’ad Alizadeh M. Faraji Gautam Choubey Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jets Scientific Reports |
| title | Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jets |
| title_full | Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jets |
| title_fullStr | Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jets |
| title_full_unstemmed | Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jets |
| title_short | Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jets |
| title_sort | numerical investigation of compressible flow around nose cone with multi row disk and multi coolant jets |
| url | https://doi.org/10.1038/s41598-023-28127-9 |
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