A Design Study and Performance Prediction of an Internal Compression Supersonic Air Intake
The aim of this research is to carryout a design study on a variable geometry rectangular supersonic air-intake at different flight conditions. The design of the air-intake at supersonic Mach number according to “on-design” condition ( ), to get a maximum total-pressure recovery, and study the perfo...
| Main Author: | |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
Unviversity of Technology- Iraq
2013-07-01
|
| Series: | Engineering and Technology Journal |
| Subjects: | |
| Online Access: | https://etj.uotechnology.edu.iq/article_82298_9ed14ec7847c0ca43e07535ae7c94aad.pdf |
| _version_ | 1797325597549002752 |
|---|---|
| author | Bahjat Hassan Alyas |
| author_facet | Bahjat Hassan Alyas |
| author_sort | Bahjat Hassan Alyas |
| collection | DOAJ |
| description | The aim of this research is to carryout a design study on a variable geometry rectangular supersonic air-intake at different flight conditions. The design of the air-intake at supersonic Mach number according to “on-design” condition ( ), to get a maximum total-pressure recovery, and study the performance of air-intake at supersonic Mach number according to “off-design” conditions ( ). The air-intake consists of convergent-divergent nozzle. The number of oblique shock waves is induced by the sharp cowl lips at the nozzle entrance and their reflections may continue along the convergent passage depending on the free-stream Mach number and nozzle wall turning angle. The location of the normal shock wave is just downstream the throat, for an “off-design” condition, and at nozzle throat, at its “on-design” condition [21]. The flow is assumed as one-dimensional compressible, and inviscid. The flow properties were calculated using the analytical method based on the relation of the oblique shock and normal shock waves. The divergent part was analyzed for different divergent lengths, to maintain the divergent angle less than value that causes flow separation and to get the maximum total pressure recovery. The convergent part was analyzed for different convergent lengths, to maintain the oblique shock and their reflected terminated before the throat position to get maximum total pressure recovery, [21]. |
| first_indexed | 2024-03-08T06:11:41Z |
| format | Article |
| id | doaj.art-a664e1a62d3149888c9c33e8d9127419 |
| institution | Directory Open Access Journal |
| issn | 1681-6900 2412-0758 |
| language | English |
| last_indexed | 2024-03-08T06:11:41Z |
| publishDate | 2013-07-01 |
| publisher | Unviversity of Technology- Iraq |
| record_format | Article |
| series | Engineering and Technology Journal |
| spelling | doaj.art-a664e1a62d3149888c9c33e8d91274192024-02-04T17:35:56ZengUnviversity of Technology- IraqEngineering and Technology Journal1681-69002412-07582013-07-0131112055207510.30684/etj.31.11A482298A Design Study and Performance Prediction of an Internal Compression Supersonic Air IntakeBahjat Hassan AlyasThe aim of this research is to carryout a design study on a variable geometry rectangular supersonic air-intake at different flight conditions. The design of the air-intake at supersonic Mach number according to “on-design” condition ( ), to get a maximum total-pressure recovery, and study the performance of air-intake at supersonic Mach number according to “off-design” conditions ( ). The air-intake consists of convergent-divergent nozzle. The number of oblique shock waves is induced by the sharp cowl lips at the nozzle entrance and their reflections may continue along the convergent passage depending on the free-stream Mach number and nozzle wall turning angle. The location of the normal shock wave is just downstream the throat, for an “off-design” condition, and at nozzle throat, at its “on-design” condition [21]. The flow is assumed as one-dimensional compressible, and inviscid. The flow properties were calculated using the analytical method based on the relation of the oblique shock and normal shock waves. The divergent part was analyzed for different divergent lengths, to maintain the divergent angle less than value that causes flow separation and to get the maximum total pressure recovery. The convergent part was analyzed for different convergent lengths, to maintain the oblique shock and their reflected terminated before the throat position to get maximum total pressure recovery, [21].https://etj.uotechnology.edu.iq/article_82298_9ed14ec7847c0ca43e07535ae7c94aad.pdfconvergentdivergent nozzlesupersonic air intakenormal and oblique shock waves |
| spellingShingle | Bahjat Hassan Alyas A Design Study and Performance Prediction of an Internal Compression Supersonic Air Intake Engineering and Technology Journal convergent divergent nozzle supersonic air intake normal and oblique shock waves |
| title | A Design Study and Performance Prediction of an Internal Compression Supersonic Air Intake |
| title_full | A Design Study and Performance Prediction of an Internal Compression Supersonic Air Intake |
| title_fullStr | A Design Study and Performance Prediction of an Internal Compression Supersonic Air Intake |
| title_full_unstemmed | A Design Study and Performance Prediction of an Internal Compression Supersonic Air Intake |
| title_short | A Design Study and Performance Prediction of an Internal Compression Supersonic Air Intake |
| title_sort | design study and performance prediction of an internal compression supersonic air intake |
| topic | convergent divergent nozzle supersonic air intake normal and oblique shock waves |
| url | https://etj.uotechnology.edu.iq/article_82298_9ed14ec7847c0ca43e07535ae7c94aad.pdf |
| work_keys_str_mv | AT bahjathassanalyas adesignstudyandperformancepredictionofaninternalcompressionsupersonicairintake AT bahjathassanalyas designstudyandperformancepredictionofaninternalcompressionsupersonicairintake |