Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1 -1.5)
<span>In this research a numerical investigation on a supersonic air intake was done. The aim of this <span>work is to investigate a variable geometry of cross-section area for supersonic air intake at range <span>(1.1 -1.5) Mach number, to get a maximum pressure recovery. In this...
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| Format: | Article |
| Language: | English |
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Tikrit University
2017-12-01
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| Series: | Tikrit Journal of Engineering Sciences |
| Subjects: | |
| Online Access: | http://www.tj-es.com/ojs/index.php/tjes/article/view/641 |
| _version_ | 1797710516783677440 |
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| author | Hasson Shaban Hamood |
| author_facet | Hasson Shaban Hamood |
| author_sort | Hasson Shaban Hamood |
| collection | DOAJ |
| description | <span>In this research a numerical investigation on a supersonic air intake was done. The aim of this <span>work is to investigate a variable geometry of cross-section area for supersonic air intake at range <span>(1.1 -1.5) Mach number, to get a maximum pressure recovery. In this work, the flow starts with a <span>normal shock attached to the intake cowl lip. The flow is assumed compressible, inviscid, twodimensional flow, unsteady, and axisymmetric. The equations (Continuity, Momentum, and Energy) <span>were solved based on a finite volume method. The governing equations were solved iteratively <span>using time marching technique. This part is analyzed for several Mach numbers, where the flow <span>properties are determined from inlet of air intake to the diffuser exit. Results show that, the <span>implementation of time marching scheme has succeeded in the prediction of the choked flow <span>region, which is important in the study of the performance of convergent-divergent diffuser. Also the <span>results indicated the absolute velocity increases along the convergent part and then start to <span>decrease along divergent part independently on the values of free-stream Mach numbers. </span></span></span></span></span></span></span></span></span></span></span> |
| first_indexed | 2024-03-12T06:52:39Z |
| format | Article |
| id | doaj.art-8e935cca42554da68a40981599860131 |
| institution | Directory Open Access Journal |
| issn | 1813-162X 2312-7589 |
| language | English |
| last_indexed | 2024-03-12T06:52:39Z |
| publishDate | 2017-12-01 |
| publisher | Tikrit University |
| record_format | Article |
| series | Tikrit Journal of Engineering Sciences |
| spelling | doaj.art-8e935cca42554da68a409815998601312023-09-03T00:11:16ZengTikrit UniversityTikrit Journal of Engineering Sciences1813-162X2312-75892017-12-012333746321Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1 -1.5)Hasson Shaban Hamood0Technical College-Mosul, Mosul,<span>In this research a numerical investigation on a supersonic air intake was done. The aim of this <span>work is to investigate a variable geometry of cross-section area for supersonic air intake at range <span>(1.1 -1.5) Mach number, to get a maximum pressure recovery. In this work, the flow starts with a <span>normal shock attached to the intake cowl lip. The flow is assumed compressible, inviscid, twodimensional flow, unsteady, and axisymmetric. The equations (Continuity, Momentum, and Energy) <span>were solved based on a finite volume method. The governing equations were solved iteratively <span>using time marching technique. This part is analyzed for several Mach numbers, where the flow <span>properties are determined from inlet of air intake to the diffuser exit. Results show that, the <span>implementation of time marching scheme has succeeded in the prediction of the choked flow <span>region, which is important in the study of the performance of convergent-divergent diffuser. Also the <span>results indicated the absolute velocity increases along the convergent part and then start to <span>decrease along divergent part independently on the values of free-stream Mach numbers. </span></span></span></span></span></span></span></span></span></span></span>http://www.tj-es.com/ojs/index.php/tjes/article/view/641Convergent-divergent diffuser, Supersonic air intake, Finite volume method, Time marching techniques |
| spellingShingle | Hasson Shaban 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, Time marching techniques |
| 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, Time marching techniques |
| url | http://www.tj-es.com/ojs/index.php/tjes/article/view/641 |
| work_keys_str_mv | AT hassonshabanhamood performancepredictionofinternalcompressionsupersonicairintakeatrangeofmachnumbers1115 |