Computational Fluid Dynamics of Whole-Body Aircraft

Agarwal, Ramesh K.

doi:10.1146/annurev.fluid.31.1.125

Cited by 47 publications

(29 citation statements)

References 47 publications

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“…Growing computer power and development of reliable numerical techniques made it possible to obtain more detailed data from numerical modeling. Currently the flow field around an entire aircraft configuration can be modeled numerically based on inviscid and viscous models (Agarwal, 1999). Utilizing the Euler equations allows to capture the global flow structure, but because viscosity is neglected it cannot predict separation related to viscous-inviscid interaction (e.g.…”

Section: Introductionmentioning

confidence: 99%

Large-eddy simulation of shock-wave/turbulent-boundary-layer interaction

2006

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Well-resolved large-eddy simulations (LES) are performed in order to investigate flow phenomena and turbulence structure of the boundary layer along a supersonic compression ramp. The numerical simulations directly reproduce an available experimental result. The compression ramp has a deflection angle of $\beta\,{=}\,25^\circ$. The mean free-stream Mach number is $M_\infty\,{=}\,2.95$. The Reynolds number based on the incoming boundary-layer thickness is $Re_{\delta_0}\,{=}\,63\,560$ in accordance with the reference experiment. These simulations overcome deficiencies of earlier direct numerical simulations (DNS) and LES in terms of ramp-deflection angle, Reynolds number and spanwise size of the computational domain which is required for capturing the essential flow phenomena. The filtered conservation equations for mass, momentum and energy are solved with a high-order finite-difference scheme. The effect of subgrid scales is modelled by the approximate deconvolution model. About $18.5\,{\times}\,10^6$ grid points are used for discretizing the computational domain. To obtain mean flow and turbulence structure the flow is sampled 1272 times over 703 characteristic time scales of the incoming boundary layer. Statistical data are computed from these samples. An analysis of the data shows good agreement with the experiment in terms of mean quantities such as shock position, separation and reattachment location, skin-friction and surface-pressure distributions, and turbulence structure. The computational data confirm theoretical and experimental results on fluctuation amplification across the interaction region. In the wake of the main shock a shedding of shocklets is observed. The temporal behaviour of the coupled shock–separation system agrees well with experimental data. Unlike previous DNS the present simulation data provide indications of a large-scale shock motion. Also, evidence for the existence of three-dimensional large-scale streamwise structures, commonly referred to as Görtler-like vortices, is found.

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Section: Introductionmentioning

confidence: 99%

Large-eddy simulation of shock-wave/turbulent-boundary-layer interaction

2006

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“…Relation (19) shows that the wavelet basis can represent a function with significantly fewer degrees of freedom, while still retaining an accuracy O(ǫ). However, in order to realize the benefits of wavelet compression, we need to be able to reconstruct u ≥ (p) from the subset N (ǫ) ⊂ N of significant grid points.…”

Section: Grid Adaptationmentioning

confidence: 99%

“…In the explicit approach considered here the surface is approximated explicitly using Delaunay triangulation and Voronoi diagrams. This approach has been popular in computer graphics [16,17], climate modelling [18] and aeronautical engineering [19]. In the implicit approach [20] the surface is first embedded in a higher dimensional computational space (e.g.…”

Section: Introductionmentioning

confidence: 99%

An adaptive wavelet collocation method for the solution of partial differential equations on the sphere

Mehra

Kevlahan

2008

Journal of Computational Physics

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A dynamic adaptive numerical method for solving partial differential equations on the sphere is developed. The method is based on second generation spherical wavelets on almost uniform nested spherical triangular grids, and is an extension of the adaptive wavelet collocation method to curved manifolds. Wavelet decomposition is used for grid adaption and interpolation. An O(N ) hierarchical finite difference scheme based on the wavelet multilevel decomposition is used to approximate Laplace-Beltrami, Jacobian and flux-divergence operators. The accuracy and efficiency of the method is demonstrated using linear and nonlinear examples relevant to geophysical flows. Although the present paper considers only the sphere, the strength of this new method is that it can be extended easily to other curved manifolds by considering appropriate coarse approximations to the desired manifold (here we used the icosahedral approximation to the sphere at the coarsest level).

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“…The participants were also requested to quantify the computational complexity of their codes: it was found that, depending on the inviscid flow model used, VII codes were one to two orders of magnitude cheaper than Navier-Stokes codes. The latter codes required 10 6 -10 7 floating-point operations per grid point; a price tag that is still representative for today's Navier-Stokes codes, as can be inferred from the review data presented by Agarwal [62].…”

Section: Application To Transonic Airfoil Flowmentioning

confidence: 99%

Matched asymptotic expansions and the numerical treatment of viscous-inviscid interaction

Veldman

2001

Practical Asymptotics

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Link to publication in University of Groningen/UMCG research database Citation for published version (APA): Veldman, A. E. P. (2001). Matched asymptotic expansions and the numerical treatment of viscous-inviscid interaction. Journal of Engineering Mathematics, 39(1-4), 189-206. CopyrightOther than for strictly personal use, it is not permitted to download or to forward/distribute the text or part of it without the consent of the author(s) and/or copyright holder(s), unless the work is under an open content license (like Creative Commons).Take-down policy If you believe that this document breaches copyright please contact us providing details, and we will remove access to the work immediately and investigate your claim. Abstract. The paper presents a personal view on the history of viscous-inviscid interaction methods, a history closely related to the evolution of the method of matched asymptotic expansions. The main challenge in solving Prandtl's boundary-layer equations has been to overcome the singularity at a point of steady flow separation. Stewartson's triple-deck theory has inspired a solution to this challenge, and thereby it paved the way for industrial use of viscous-inviscid interaction methods.

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Computational Fluid Dynamics of Whole-Body Aircraft

Cited by 47 publications

References 47 publications

Large-eddy simulation of shock-wave/turbulent-boundary-layer interaction

Large-eddy simulation of shock-wave/turbulent-boundary-layer interaction

An adaptive wavelet collocation method for the solution of partial differential equations on the sphere

Matched asymptotic expansions and the numerical treatment of viscous-inviscid interaction

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