Effects of Different Thickness Variation Strategies on Dynamic Stall in an Oscillating Airfoil

Hamdani, Hossein; Riaz, Rizwan; Qureshi, Humayun; Parvez, Khalid; Naqvi, Muhammad Ali; Sheikh, Shakil R.

doi:10.2514/6.2006-3691

Cited by 1 publication

(1 citation statement)

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“…Being an algebraic model, it uses Boussinesq's eddy viscosity approximation to compute the Reynolds stress tensor as the product of an eddy viscosity and the mean strain rate tensor in terms of mixing length. The model is chosen in the present flow simulations considering its less computational cost being a zero equation model and keeping in view its past success in modeling static stall and DS [28,29,[31][32][33]38], although Ekaterinaris [18,19] in his study has preferred the Baldwin-Barth [39] model over others including Baldwin-Lomax. In the current simulations in which the flow is expected to be attached or slightly separated, the use of the Baldwin-Lomax model is appropriate.…”

Section: Turbulence Modelingmentioning

confidence: 99%

CFD analysis of an oscillating wing at various reduced frequencies

Farooq

Hamdani

Anwar-ul-Haque³

et al. 2008

Numerical Methods in Fluids

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SUMMARYThe effect of various reduced frequencies has been examined for an oscillating aspect ratio 10 NACA 0015 wing. An unsteady, compressible three-dimensional (3D) Navier-Stokes code based on Beam and Warming algorithm with the Baldwin-Lomax turbulence model has been used. The code is validated for the study against published experimental data. The 3D unsteady flow field is simulated for reduced frequency values of 0.1, 0.2 and 0.3 for a fixed mean angle of attack position and fixed amplitude. The type of motion is sinusoidal harmonic. The force coefficients, pressure distributions and flow visualization show that at the given conditions the flow remains attached to the wing surface even at high angles of attack with no clear separation or typical light-to-deep category of dynamic stall. Increased magnitude of hysteresis and higher gradients are seen at higher reduced frequencies. The 3D effects are even found at midspan locations. In addition, the rate of decrease in lift near the wing tips compared with the wing root is not much like in the static cases.

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