Abstract
The primary objective of this study is to capture the skin friction lines as the impression of primary and secondary vortices on the upper surface of a slender sharp edged 65¡ delta wing model at low speed subsonic static test condition using oil flow visualization. Subsequently CFD (computational fluid dynamics) analysis is carried out using CFD code Ansys Fluent. Multi block structured meshes are generated within the computational domain and Reynolds Averaged Navier Stokes (RANS) based steady state three dimensional CFD simulations are performed. The experimental and computational results are compared both qualitatively and quantitatively in the context of surface skin friction topography and vortex breakdown.
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