Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1-1.5)
In this research, a numerical investigation on a supersonic air intake was done. The aim of this work is to investigate a variable geometry of cross-section area for supersonic air intake at range (1.1-1.5) Mach number, to get a maximum pressure recovery. In this work, the flow starts with a normal...
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| Format: | Article |
| Language: | English |
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Tikrit University
2016-09-01
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| Series: | Tikrit Journal of Engineering Sciences |
| Subjects: | |
| Online Access: | http://tj-es.com/vol23no3pa4/ |
| _version_ | 1797727235463970816 |
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| author | Hasson S. Hamood |
| author_facet | Hasson S. Hamood |
| author_sort | Hasson S. Hamood |
| collection | DOAJ |
| description | In this research, a numerical investigation on a supersonic air intake was done. The aim of this work is to investigate a variable geometry of cross-section area for supersonic air intake at range (1.1-1.5) Mach number, to get a maximum pressure recovery. In this work, the flow starts with a normal shock attached to the intake cowl lip. The flow is assumed compressible, inviscid, two-dimensional flow, unsteady, and axisymmetric. The equations (Continuity, Momentum, and Energy) were solved based on a finite volume method. The governing equations were solved iteratively using time marching technique. This part is analyzed for several Mach numbers, where the flow properties are determined from inlet of air intake to the diffuser exit. Results show that, the implementation of time marching scheme has succeeded in the prediction of the choked flow region, which is important in the study of the performance of convergent-divergent diffuser. Also the results indicated the absolute velocity increases along the convergent part and then start to decrease along divergent part independently on the values of free-stream Mach numbers. |
| first_indexed | 2024-03-12T10:56:56Z |
| format | Article |
| id | doaj.art-e74797737958423da744d30619c1b2a2 |
| institution | Directory Open Access Journal |
| issn | 1813-162X |
| language | English |
| last_indexed | 2024-03-12T10:56:56Z |
| publishDate | 2016-09-01 |
| publisher | Tikrit University |
| record_format | Article |
| series | Tikrit Journal of Engineering Sciences |
| spelling | doaj.art-e74797737958423da744d30619c1b2a22023-09-02T06:14:56ZengTikrit UniversityTikrit Journal of Engineering Sciences1813-162X2016-09-012333746Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1-1.5)Hasson S. Hamood0Technical College, Mosul, IraqIn this research, a numerical investigation on a supersonic air intake was done. The aim of this work is to investigate a variable geometry of cross-section area for supersonic air intake at range (1.1-1.5) Mach number, to get a maximum pressure recovery. In this work, the flow starts with a normal shock attached to the intake cowl lip. The flow is assumed compressible, inviscid, two-dimensional flow, unsteady, and axisymmetric. The equations (Continuity, Momentum, and Energy) were solved based on a finite volume method. The governing equations were solved iteratively using time marching technique. This part is analyzed for several Mach numbers, where the flow properties are determined from inlet of air intake to the diffuser exit. Results show that, the implementation of time marching scheme has succeeded in the prediction of the choked flow region, which is important in the study of the performance of convergent-divergent diffuser. Also the results indicated the absolute velocity increases along the convergent part and then start to decrease along divergent part independently on the values of free-stream Mach numbers.http://tj-es.com/vol23no3pa4/Convergent-divergent diffuserSupersonic air intakeFinite volume method |
| spellingShingle | Hasson S. Hamood Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1-1.5) Tikrit Journal of Engineering Sciences Convergent-divergent diffuser Supersonic air intake Finite volume method |
| title | Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1-1.5) |
| title_full | Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1-1.5) |
| title_fullStr | Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1-1.5) |
| title_full_unstemmed | Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1-1.5) |
| title_short | Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1-1.5) |
| title_sort | performance prediction of internal compression supersonic air intake at range of mach numbers 1 1 1 5 |
| topic | Convergent-divergent diffuser Supersonic air intake Finite volume method |
| url | http://tj-es.com/vol23no3pa4/ |
| work_keys_str_mv | AT hassonshamood performancepredictionofinternalcompressionsupersonicairintakeatrangeofmachnumbers1115 |