ON SIMULATING ACOUSTIC-SHOCK WAVES INTERACTION | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 104, Volume 10, 10th International Conference On Aerospace Sciences & Aviation Technology, May 2003, Page 973-984 PDF (1.38 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.2001.59778 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
| KHALID M. HOSNY1; ISMAIL A. ISMAIL2; AWATEF A. NAMED3 | ||||
| 1Lecturer, Dept. of Computer Science, College of Computers & Informatics, Zagazig University, Zagazig, Egypt. | ||||
| 2Professor, Dept. of _Computer Science and Dean of College of Computers & Informatics, Zagazig University, Zagazig, Egypt. | ||||
| 3Professor, Dept. of Aerospace Engineering & Engineering Mechanics, College of Engineering, University of Cincinnati, Cincinnati, Ohio, USA. | ||||
| Abstract | ||||
| Numerical simulation of acoustic-shock waves interaction in quasi-one dimensional convergent-divergent nozzles is performed. The time dependent nature of flow field is initiated by using very small amplitude acoustic wave that incident on the inlet of the nozzle. Computations are performed using 3-point fourth-order compact implicit McCormick-type scheme to approximate the spatial derivatives and the two steps 5-6 alternating 2-N storage Low-Dispersion and —Dissipation Runge-Kutta (LDDRK) method as a time marching scheme. Artificial damping terms were used in damping non-physical very high wave numbers waves. The obtained numerical solutions with acoustic perturbation are presented. | ||||
| Keywords | ||||
| Aeroacoustics; compact schemes; Runge-Kutta; Fourier transform | ||||
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