Numerical analysis of leading edge vortical flow on 65 degree delta wing. | [Proceedings 5th International Bhurban Conference on Applied Sciences and Technology • 2007]

Author(s):

1. Anwar-Ul-Haque: Center of Excellences in Science and Applied Technologies (CESAT), Islamabad, Pakistan

2. Jawad Khawar: Center of Excellences in Science and Applied Technologies (CESAT), Islamabad, Pakistan

3. Abdul-Jabbar: Center of Excellences in Science and Applied Technologies (CESAT), Islamabad, Pakistan

4. Sajid Raza Ch.: Center of Excellences in Science and Applied Technologies (CESAT), Islamabad, Pakistan

Abstract:

This paper describes a computational study of the effect of Mach number and string fairing on the flow over a 65° delta wing geometry at two moderate angles of attack and at fixed Reynolds number. Trajectory of the mean primary, secondary and tertiary vortex cores were plotted to evaluate the capabilities of different turbulence models. Qualitative and quantitative comparison with experimental data of pressure distribution was done and SST model results have accurately predicted the onset of flow separation and quantity of flow separation. Moreover, it was found that an increase in Mach number in subsonic region for sharp leading edge promotes the leading edge vortical flow.

Page(s): 22-33

DOI: DOI not available

Published: Journal: Proceedings 5th International Bhurban Conference on Applied Sciences and Technology , Volume: 0, Issue: 0, Year: 2007

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