Effect of Shapes and Turbulent Inlet Flow to Vortices on Delta Wings

Abstract:

This paper aims to estimate the effect of turbulent inlet flow to vortices on Delta wing with four different turbulence intensity from 0.5% to 15% and the effect of taper ratios to aerodynamic characteristics of Delta wings with four taper ratios: 0, 0.1, 0.2, 0.3, 0.4, 0.5, 0.6, 0.7. The main purpose of this paper is to find out the formation, development, and breakdown of vortices on Delta wings when changing taper ratios and turbulence intensity thence determining the center of vortices with the range of attack angles from 5o to 40o in low velocities about 2.5 m/s. This research uses Delta wing models with a 40o swept-back leading edge, the root chord length 150 mm, and a thickness 5 mm. The problem is simulated by using ANSYS fluent and experiment in the subsonic wind tunnel to compare and validate results. The Delta wing models are meshed by using ICEM to improve the mesh quality and using the turbulence model for low Reynolds number flows Transition SST (4 equations) to calculate aerodynamic characteristics such as lift coefficient, drag coefficient, pressure coefficient... find the paths which connect centers of the vortices, and show the contours of pressures and velocities to evaluate the change of centers of the vortices. The results showed that the two vortices grow up and tend to move inward when the attack angle increase, the vortices are broken strongly in high attack angles, the aerodynamic quality of Delta wings change insignificantly when changing turbulent intensity at inlet. This research also carried out that the stall angle increase when increasing the taper ratio.

• Periodical: Applied Mechanics and Materials (Volume 889)
• Pages: 434-439
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.889.434
• Online since: March 2019
• Authors: Ngoc Khanh Tran, Van Khang Nguyen, Phu Khanh Nguyen, Thi Kim Dung Hoang*, Van Quang Dao
• Keywords: ANSYS, Delta Wing, Low Reynolds Number, Taper Ratio, Turbulent Inlet, Vortices

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