The effects of 2D surface roughness on the aerodynamic performance of the NACA0012 airfoil (Re = 5 ×104, AoA = 10°) are investigated with direct numerical simulations (DNS). The DNS are performed with an energy-conservative fourth-order parallel code solving the incompressible Navier-Stokes equations in generalized curvilinear coordinates. Located near the leading edge, the surface roughness elements are characterized with streamwise sinusoidal-wave geometry that is uniform in the spanwise direction but with varying wave number (from k = 0 to 12, with k = 0 corresponding to the smooth case, chosen as the baseline). The flow structures and and boundary layer separation are quantified, and it is shown that the lift and drag coefficients are strongly affected by separation bubbles that arise. The numerical results reveal that the drag coefficients increase to a peak value and then decrease with increase in wave number, while the lift coefficients decreases strongly for k ≤ 6 and then become stable. The boundary layer separation is affected by the wavenumber and with an increase in the number of separation bubbles that render the flow more complex. For k ≥ 8, massive separation occurs and almost covering the suction side of the airfoil dominating the airfoil aerodynamic performance.
|Title of host publication
|21st Australasian Fluid Mechanics Conference, AFMC 2018
|Australasian Fluid Mechanics Society
|Published - Jan 1 2018
Bibliographical noteKAUST Repository Item: Exported on 2020-10-09
Acknowledged KAUST grant number(s): URF/1/1394-01
Acknowledgements: The work was supported by the KAUST office of Competitive Research Funds under Award No. URF/1/1394-01 and baseline research funds of R. Samtaney. The Shaheen-Cray XC40 at KAUST was utilized for all the simulations.