High Resolution Turbulence Treatment of F/A-18 Tail Buffet

Morton, Scott A.; Cummings, Russell M.; Kholodar, Denis B.

doi:10.2514/1.29577

Cited by 31 publications

(9 citation statements)

References 19 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Unstructured grid methodology offers significant advantage in terms of grid generation and has been gaining popularity in the CFD community in recent years with an increasing emphasis on solving unsteady viscous flow over complex configurations, as evidenced by the recent publications appearing in the literature. [7][8][9][10][11][12][13] For the current work, we make use of a widely-distributed, unstructured-grid flow solver FUN3D, 14 where the Navier-Stokes equations supplemented by turbulence models are solved to simulate the viscous unsteady flow field for configurations of interest. The FUN3D code has been used for many large-scale applications in the past.…”

Section: Introductionmentioning

confidence: 99%

Application of FUN3D Solver for Aeroacoustic Simulation of a Nose Landing Gear Configuration

Vatsa

Lockard

Khorrami

2011

17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference)

View full text Add to dashboard Cite

Numerical simulations have been performed for a nose landing gear configuration corresponding to the experimental tests conducted in the Basic Aerodynamic Research Tunnel at NASA Langley Research Center. A widely used unstructured grid code, FUN3D, is examined for solving the unsteady flow field associated with this configuration. A series of successively finer unstructured grids has been generated to assess the effect of grid refinement. Solutions have been obtained on purely tetrahedral grids as well as mixed element grids using hybrid RANS/LES turbulence models. The agreement of FUN3D solutions with experimental data on the same size mesh is better on mixed element grids compared to pure tetrahedral grids, and in general improves with grid refinement. Nomenclature BART Basic Aerodynamic Research Tunnel BDF backward differencing formulation BDF2 second-order backward differencing formulation BDF2OPT optimized second-order backward differencing formulation CFD computational fluid dynamics DES detached eddy simulation DDES delayed detached eddy simulation FW-H Ffowcs Williams-Hawkings HRLES hybrid RANS/LES LaRC Langley Research Center LES large eddy simulation MDDES modified delayed detached eddy simulation NLG nose landing gear PDCC partially-dressed closed-cavity PSD power spectral density PIV particle image velocimetry RANS Reynolds-averaged Navier-Stokes SPL sound pressure level SST shear stress transport TKE turbulence kinetic energy UFAFF University of Florida Aeroacoustic Facility URANS unsteady Reynolds-averaged Navier-Stokes u, v, w Cartesian fluid velocity components x, y, z Cartesian coordinates Z-vort spanwise vorticity Superscript: perturbation quantity (e.g. u = u − u ∞)

show abstract

Section: Introductionmentioning

confidence: 99%

Application of FUN3D Solver for Aeroacoustic Simulation of a Nose Landing Gear Configuration

Vatsa

Lockard

Khorrami

2011

17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference)

View full text Add to dashboard Cite

show abstract

“…The hybridization of a classic industry RANS model with ERS, for a flow of practical aerospace relevance was inspirational to many -including the current authors. Very soon after this, work emerged at the US Air Force Laboratory applying the approach to full fighter aircraft configurations, culminating in agreement between real flight test data for tail buffet [9]. Considerable campaigns on missile base flows were also carried out along with landing gear and wings with flaps at high angles [10] to name but a few.…”

Section: Eddy Resolving Simulation Costmentioning

confidence: 99%

Eddy resolving simulations in aerospace – Invited paper (Numerical Fluid 2014)

Tucker

Tyacke

2016

Applied Mathematics and Computation

View full text Add to dashboard Cite

a b s t r a c tThe future use of eddy resolving simulations (ERS) such as Large Eddy Simulation (LES), Direct Numerical Simulation (DNS) and related approaches in aerospace is explored. The turbulence modeling requirements with respect to aeroengines and aircraft is contrasted. For the latter, higher Reynolds numbers are more prevalent and this especially gives rise to the need for the hybridization of ERS methods with Reynolds Averaged Navier-Stokes (RANS) approaches. Zones where future use of pure ERS methods is now possible and those where hybridizations with RANS will be needed is outlined. The major focus is the aeroengine for which the component scales are much smaller. This gives rise to generally more benign Reynolds numbers. The use of eddy resolving methods in a wide range of zones in an aeroengine is discussed and the potential benefits and also cost drawbacks with such approaches noted. The tension when using such computationally intensive calculations in an area where the coupling of components and even the airframe and engine is becoming increasingly important is explored. Also, the numerical methods and meshing requirements are considered and the implications of ERS methods for future numerical algorithms. It is postulated that such simulations are ready now for niche uses in industry. However, to perform the scale of simulations that industry requires, to meet pressing environmental needs, challenges remain. For example, there is the need to develop optimal numerical methods that both map to the accuracy requirements for ERS and also future computer architectures.

show abstract

“…There are plenty of choices in FUN3D for turbulence models. For steady calculations, we mainly use one-equation Spalart-Allmaras (SA) [11] mode in conjunction with the solid-body rotation modification of Dacles-Mariani et al [2]. For unsteady simulations, following Vatsa et al, a modified Delayed Detached Eddy Simulation methodology was utilized [12].…”

Section: B Turbulence Modelsmentioning

confidence: 99%

“…Due to the development of computational technique and computational algorithm, more and more investigation has been done by computational fluid dynamics tools to investigate the buffet phenomena of the twin-tail fighter, e.g., F-15 and F/A-18. [1][2][3][4][5]10].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamics of the F-15 At High Angle of Attack

Yang

Chen

Wang

et al. 2015

53rd AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

In this paper, the unstructured-grid flow solver, FUN3D, is used to compute the aerodynamic performance of F-15. A half model of F-15 with 14 million grid points is used for both steady and unsteady computations. The Detached Eddy Simulation (DES) method based on the Spalart-Allmaras (SA) turbulence model is used in the unsteady computation of the F-15 with high angle of attack. Computational results for the transonic steady cases of the F-15 vertical tail and the benchmark case of a cylinder in a cross flow are presented, showing excellent agreement with other numerical results and experimental measurements in the literature. Furthermore, unsteady pressure fluctuations on the F-15 vertical tail at a high angle of attack (22) are computed. The effect of the far field turbulence on the power spectrum of the pressure is studied, and the optimal turbulence level is determined to capture the dominant regime of the power spectrum of the pressure measured in wind tunnel tests. The FUN3D computation is thus expected to provide reliable pressure data for the prediction of the buffeting response of the F-15 vertical tail.

show abstract

High Resolution Turbulence Treatment of F/A-18 Tail Buffet

Cited by 31 publications

References 19 publications

Application of FUN3D Solver for Aeroacoustic Simulation of a Nose Landing Gear Configuration

Application of FUN3D Solver for Aeroacoustic Simulation of a Nose Landing Gear Configuration

Eddy resolving simulations in aerospace – Invited paper (Numerical Fluid 2014)

Aerodynamics of the F-15 At High Angle of Attack

Contact Info

Product

Resources

About