Compuational Analysis of the Flow on a Subsonic Delta-Wing

A computational study for a delta-wing which has 65 degrees sweep back angle is performed using Stress-Blended Eddy Simulation Wall-Adapting Local Eddy-viscosity (SBES-WALE) turbulence model. The surface pressure on the wing and the pressure distribution in the vortex structures are examined to analyze the characteristics of the transient flow at different angle of attacks. The transient flow phenomena on the subsonic delta-wing has been analyzed, including the frequencies and influence of the vortex shedding and breakdown. The surface pressure distribution on the wing has been generally consistent with reference experiment, while the flow phenomena related with secondary vortex and vortex breakdown has discrepancies. Also, the vortex breakdown frequency has been observed to coincide with the lift oscillation frequency, at 23 degrees of angle of attack. This study intends to contribute to the understanding of the leading-edge-vortex flows related with the high angle-of-attack flight.