Shock-induced heating and transition to turbulence in a hypersonic boundary layer

Fu, Lin; Karp, Michael; Bose, Sanjeeb; Moin, Parviz; Urzay, Javier

doi:10.1017/jfm.2020.935

Cited by 70 publications

(48 citation statements)

References 62 publications

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“…Time advancement is performed using a three stage explicit Runge-Kutta scheme (Gottlieb, Shu, & Tadmor, 2001), and the spatial discretization is formally second-order accurate. The code has been extensively validated, and recent applications of the code could be found in Bres et al (2018), Lozano-Duran et al ( 2020) and Fu, Karp, Bose, Moin, and Urzay (2021). Alya is a parallel, multiscale simulation code developed at the Barcelona Supercomputing Centre (Vazquez et al, 2016).…”

Section: Flow Solvers and Numerical Methodsmentioning

confidence: 99%

Large eddy simulation of aircraft at affordable cost: a milestone in computational fluid dynamics

Goc

Lehmkuhl

Park

et al. 2021

Flow

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While there have been numerous applications of large eddy simulations (LES) to complex flows, their application to practical engineering configurations, such as full aircraft models, have been limited to date. Recently, however, advances in rapid, high quality mesh generation, low-dissipation numerical schemes and physics-based subgrid-scale and wall models have led to, for the first time, accurate simulations of a realistic aircraft in landing configuration (the Japanese Aerospace Exploration Agency Standard Model) in less than a day of turnaround time with modest resource requirements. In this paper, a systematic study of the predictive capability of LES across a range of angles of attack (including maximum lift and post-stall regimes), the robustness of the predictions to grid resolution and the incorporation of wind tunnel effects is carried out. Integrated engineering quantities of interest, such as lift, drag and pitching moment will be compared with experimental data, while sectional pressure forces will be used to corroborate the accuracy of the integrated quantities. Good agreement with experimental $C_L$ data is obtained across the lift curve with the coefficient of lift at maximum lift, $C_{L,max}$ , consistently being predicted to within five lift counts of the experimental value. The grid point requirements to achieve this level of accuracy are reduced compared with recent estimates (even for wall modelled LES), with the solutions showing systematic improvement upon grid refinement, with the exception of the solution at the lowest angles of attack, which will be discussed later in the text. Simulations that include the wind tunnel walls and aircraft body mounting system are able to replicate important features of the flow field noted in the experiment that are absent from free air calculations of the same geometry, namely, the onset of inboard flow separation in the post-stall regime. Turnaround times of the order of a day are made possible in part by algorithmic advances made to leverage graphical processing units. The results presented herein suggest that this combined approach (meshing, numerical algorithms, modelling, efficient computer implementation) is on the threshold of readiness for industrial use in aeronautical design.

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Section: Flow Solvers and Numerical Methodsmentioning

confidence: 99%

Large eddy simulation of aircraft at affordable cost: a milestone in computational fluid dynamics

Goc

Lehmkuhl

Park

et al. 2021

Flow

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“…3(a) in ( 7)). However, in diabatic (with heat transfer) boundary layers and channel flows, the transformation fails and the incompressible law of the wall is not recovered (4,(8)(9)(10)(11)(12)(13).…”

Section: S +mentioning

confidence: 99%

“…Prior numerical evidence supports this criticism. Although the transformation has been successful in channel flows even in the log region (see (4,5,12,13,20)), it has displayed some variability in the log intercepts of transformed velocity profiles from adiabatic boundary layers, and the variability is even more pronounced in diabatic boundary layers (see (8)(9)(10)(11)). In all of these cases, the transformation performs well in the viscous sublayer where the viscous stress τv > τR, but in boundary layers it is less successful in the log region where τR > τv.…”

Section: R a F Tmentioning

confidence: 99%

Velocity transformation for compressible wall-bounded turbulent flows with and without heat transfer

Griffin,

Fu,

Moin

2021

Preprint

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“…Inside these combustion devices, an intricate interplay between shocks and streams of reactants yields a stable power output. A great number of scientific studies has been performed to clarify many relevant details of this kind of compressible problems, including shock interactions with canonical turbulence [4][5][6][7][8], planar interactions with gaseous interfaces [9][10][11], shock-shock interactions [12,13], shock reflections on solid walls [14][15][16][17] and boundary-layer effects [18][19][20][21][22] that may include separation processes [23,24], or transmission of flow discontinuities across tangential layers [25][26][27], to name a few.…”

Section: Introductionmentioning

confidence: 99%

“…The mechanical disquisitions over the equilibrium and dynamics of high-speed flows have long benefited from theoretical approximations of ideal flow [28,29] and small-perturbation methods [30,31]. In addition, further efforts to include real-flow effects have shed light on viscous processes in the related mechanics [32][33][34][35][36]24] as well as thermal and thermochemical non-equilibrium [37]. However, besides few studies on one-dimensional [38][39][40] and two dimensional waves [41], ideal-gas and calorically-perfect assumptions have been adopted in the vast majority of the analyses of compressible continuum-model fluids.…”

Section: Introductionmentioning

confidence: 99%

Specific heat effects in two-dimensional shock refractions

et al. 2021

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Compressible mixtures in supersonic flows are subject to significant temperature changes via shock-waves and expansions, which affect several properties of the flow. Besides the widely-studied variable transport effects such as temperature-dependent viscosity and conductivity, vibrational and rotational molecular energy storage is also modified through the variation of the heat capacity c p and heat capacity ratio γ, specially in hypersonic flows. Changes in the composition of the mixture may also modify its value through the species mass fraction Y α , thereby affecting the compression capacity of the flow. Canonical configurations are studied here to explore their sharply-conditioned mechanical equilibrium under variations of these thermal models. In particular, effects of c p (T, Y α ) and γ(T, Y α ) on the stability of shock-impinged supersonic shear and mixing layers is addressed, on condition that a shock wave is refracted. It is found that the limits defining regular structures are affected (usually broadened out) by the dependence of heat capacities with temperature. Theoretical and high-fidelity numerical simulations exhibit a good agreement in the prediction of regular shock reflections and their post-shock aerothermal properties.

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Shock-induced heating and transition to turbulence in a hypersonic boundary layer

Abstract: Abstract

Cited by 70 publications

References 62 publications

Large eddy simulation of aircraft at affordable cost: a milestone in computational fluid dynamics

Large eddy simulation of aircraft at affordable cost: a milestone in computational fluid dynamics

Velocity transformation for compressible wall-bounded turbulent flows with and without heat transfer

Specific heat effects in two-dimensional shock refractions

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