- All Journals
- Al-Qadisiyah University
- Basrah University
- Kirkuk University
- Mosul University
- The Iraqi Borad for Medical Specialization
- University of Anbar
- University of Technology
- Al Mustafa University
- Al-Zahraa University for Women
- Alnoor University
- Kunooz University
- Misan University
- Ninevah University
- Tikrit University
- University of Al-Hamdaniya
- University of Kerbala
Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1-1.5) | ||
| Tikrit Journal of Engineering Sciences | ||
| Article 1, Volume 23, Issue 3, 2016, Pages 37-46 PDF (0 K) | ||
| Author | ||
| Hasson Shaban Hamood | ||
| Abstract | ||
| 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, twodimensional 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. | ||
| Keywords | ||
| Convergent; divergent diffuser; Supersonic Air Intake; Finite volume method; Time marching techniques | ||
|
Statistics Article View: 234 PDF Download: 134 |
||