Blowing Effects on the Separated Flow over a Moderately Swept Missile Fin

Riou, Jacques; Garnier, Éric; Basdevant, C.

doi:10.2514/1.j050082

Cited by 6 publications

(2 citation statements)

References 30 publications

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“…It has been demonstrated, consistently with the experimental works of Williams et al [7] in the case of a 50 sweep delta wing in the subsonic regime, that an optimal forcing frequency can be found. This nondimensional frequency F (with F f c=U 1 ) equals 1.5 and has been identified in [6] as being the one of the natural vortex shedding. Nevertheless, such control strategies would necessitate in practice a complex pneumatic system inside the fin that is not easy to manufacture.…”

Section: Introductionmentioning

confidence: 90%

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Control of Separated Flow over Swept Missile Fin Using Pitching Oscillations

2011

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Section: Introductionmentioning

confidence: 90%

“…The angle of attack equals 25 . This study constitutes a follow up of [6], where the reference computation has been successfully validated against these experimental data. Moreover, continuous and pulsed blowing and synthetic jets have been imposed at the leading edge of the fin.…”

Section: Introductionmentioning

confidence: 99%

Control of Separated Flow over Swept Missile Fin Using Pitching Oscillations

2011

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Experiences with two detached eddy simulation approaches through use of a high‐order finite volume solver

Cengiz

Özyörük

2020

Numerical Methods in Fluids

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SummaryIn the present study, two advanced detached eddy simulation (DES) approaches, shear‐layer‐adapted delayed DES and zonal DES in mode II, which are known to help transition from RANS to LES mode, are employed in various flow problems in conjunction with a high‐order finite volume solver. The numerical scheme, being only applicable on structured grids, has low‐dissipation and low‐dispersion features. Such features benefit mostly in the LES mode, minimizing the interference of numerical diffusion with subgrid eddy viscosity. First, corresponding subgrid models are validated via decaying homogeneous turbulence benchmark case. Then, a channel flow problem is chosen to examine these models in attached flow situations. Finally, flow around an airfoil at low Reynolds number is solved using the shear‐layer‐adapted delayed DES approach only, in an aim to obtain trailing‐edge noise spectrum at an observer location. Despite some log‐layer mismatch over turbulent boundary layers, which is typical of most DES methods, the combined application of high‐resolution numerical method and advanced DES approaches, which are implemented on a stabilized Spalart‐Allmaras turbulence model, shows merit in resolution of turbulence in regions of interest.

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