Transition and Turbulence Modelling for Dynamic Stall and Buffet

Geißler, W.; Ruiz-Calavera, Luis P.

doi:10.1016/b978-008043328-8/50065-5

Cited by 10 publications

(7 citation statements)

References 7 publications

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“…The amplitude of lift scillations at M  =0.75 was 0.35. This agrees well with the value of 0.37 obtained in [18] using the Spalart-Allmaras and Baldwin-Lomax turbulence models. , where F is the normal force, 3 flow past a 18% thick circular-arc airfoil at zero angle of attack and Re=1.110 7 .…”

Section: Resultssupporting

confidence: 81%

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Transonic flow past a Whitcomb airfoil with a deflected aileron

Kuzmin¹

2013

International Journal of Aeronautical and Space Sciences

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The sensitivity of transonic flow past a Whitcomb airfoil to deflections of an aileron is studied at free-stream Mach numbers from 0.81 to 0.86 and vanishing or negative angles of attack. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver using the k-ω SST turbulence model. The numerical study demonstrates the existence of narrow bands of the Mach number and aileron deflection angles that admit abrupt changes of the lift coefficient at small perturbations. In addition, computations reveal free-stream conditions in which the lift coefficient is independent of aileron deflections of up to 5 degrees. The anomalous behavior of the lift is explained by interplay of local supersonic regions on the airfoil. Both stationary and impulse changes of the aileron position are considered.

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Section: Resultssupporting

confidence: 81%

“…The amplitude of lift coefficient oscillations at M  =0.75 was 0.35. This agrees well with the value of 0.37 obtained numerically in [18] using the Spalart-Allmaras and Baldwin-Lomax turbulence models.…”

Section: Resultssupporting

confidence: 81%

Transonic flow past a Whitcomb airfoil with a deflected aileron

Kuzmin¹

2013

International Journal of Aeronautical and Space Sciences

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“…The numerical simulation of transonic flow was performed principally on a mesh of 1:8 Â 10 5 grid points which were clustered at the shock locations, in the near wake, and in the boundary layer. The high accuracy of the solutions was confirmed by the mesh-independence study, as discussed below, and also by solving the buffet problem for the 18% circular-arc airfoil and comparison with results available in the literature [17,18]. computations revealed self-sustained oscillations of shock waves and separated boundary layers at the airfoil aft.…”

Section: Formulation Of the Problem And A Numerical Methodssupporting

confidence: 65%

“…Frequencies of the oscillations were of the same order as those documented in previous studies of transonic buffet for a circular-arc airfoil [17,18] and wavy airfoils [19]. When c 6 8 the local curvature of the airfoil (2) is not small enough in the midchord region to trigger flow bifurcations [13,20].…”

Section: Introductionmentioning

confidence: 63%

Bifurcations and buffet of transonic flow past flattened surfaces

Kuzmin

2009

Computers & Fluids

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“…The developed solver was validated by running a few benchmark problems, e.g., the one of a transonic flow past an 18% thick circular-arc airfoil. A comparison of the obtained frequencies and amplitudes of self-sustained oscillations with available experimental and numerical data for this airfoil [14,15] demonstrated the high accuracy of the solver. For instance, at Re = 11 · 10 6 , α = 0, and gradually decreasing M ∞ , the computations showed a buffet onset in the range 0.723 M ∞ 0.780.…”

Section: Introductionmentioning

confidence: 68%