Simulation of Boundary Layer Transition on Elliptic Cones in Hypersonic Flow

Bartkowicz, Matthew D.; Subbareddy, Pramod K.; Candler, Graham V.

doi:10.2514/6.2010-1064

Cited by 16 publications

(12 citation statements)

References 10 publications

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“…Zhong (1999) performed a DNS study on the receptivity of a three-dimensional Mach-15 boundary layer to free-stream acoustic disturbances for a blunt 2:l elliptic cone. More recently, Bartkowicz et al (2010b) presented DNS results of the transition in a Mach-8 boundary layer over a sharp 4:1 elliptic cone. Acoustic noise was added into the free stream to model the experimental conditions.…”

Section: Three-dimensional and Complex Boundary Layersmentioning

confidence: 99%

Direct Numerical Simulation on the Receptivity, Instability, and Transition of Hypersonic Boundary Layers

Zhong

Wang

2012

Annu. Rev. Fluid Mech.

298

118

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The prediction of the laminar-turbulent transition of boundary layers is critically important to the development of hypersonic vehicles because the transition has a first-order impact on aerodynamic heating, drag, and vehicle operation. The success of transition prediction relies on a fundamental understanding of the relevant physical mechanisms. In the 20 years since the review by Kleiser & Zang (1991) on the direct numerical simulation (DNS) of the boundary-layer transition, significant progress has been made on DNS in the hypersonic flow regime and in the spatial DNS approach. Many high-order shock-capturing and shock-fitting finite-difference methods have been developed and extensively applied to numerical simulations of the hypersonic boundary-layer transition. DNS has become a powerful research tool and has led to discoveries of new transition mechanisms. This article reviews the recent progress of DNS on hypersonic boundary-layer receptivity, instability, and transition. The current status and future directions are also presented. 527 Annu. Rev. Fluid Mech. 2012.44:527-561. Downloaded from www.annualreviews.org by University of California -Los Angeles (Young Research Library) on 01/04/12. For personal use only. Receptivity mechanisms Transient growth B Increasing disturbance level Figure 1Paths to boundary-layer transition with respect to the disturbance amplitude. Path A, three-stage-transition mechanism in a weak-disturbance environment; path B, three-stage-transition mechanism including weak transient growth; paths C and D, transition mechanisms with strong transient growth; path E, bypass transition to very strong disturbance. Figure taken from Reshotko (

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Section: Three-dimensional and Complex Boundary Layersmentioning

confidence: 99%

Direct Numerical Simulation on the Receptivity, Instability, and Transition of Hypersonic Boundary Layers

Zhong

Wang

2012

Annu. Rev. Fluid Mech.

298

118

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“…Evidence has been accumulated regarding laminar-turbulent transition scenarios on elliptic cones at aspect ratios 2:1 and 4:1, exposed at zero angle of attack to oncoming flows for Mach numbers (Ma) between 4 and 8 in different experimental facilities, 1,2,3,4 while recently large-scale computations of the same phenomenon have appeared in the literature. 5 All these studies reported the formation of large structures near the minor axis center-line of the cone; these structures were first experimentally found by Schmisseur et al…”

Section: Introductionmentioning

confidence: 94%

“…The two-dimensional global linear eigenvalue problem (called here BiGlobal analysis 18 ) results show unstable modes in both cases. Recent large-scale computations by Bartkowicz et al 5 confirm the co-existence of all these scenarios and attempt a first classification of their significance at different Reynolds number (Re) range: while the center-line structures lead flow to transition at lower Re values, cross-flow instability near the elliptic cone leading-edge becomes competitive at higher Reynolds numbers. The origin and role of the large center-line structures in the laminar-turbulent transition process on the elliptic cone is presently unclear.…”

Section: Introductionmentioning

confidence: 99%

Spatial linear global instability analysis of the HIFiRE-5 elliptic cone model flow

Gonzalez

Theofilis

2013

43rd Fluid Dynamics Conference

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The linear instability of the three-dimensional boundary-layer over the HIFiRE-5 flight test geometry, i.e. a rounded-tip 2:1 elliptic cone, at Mach 7, has been analyzed through spatial BiGlobal analysis, in a effort to understand transition and accurately predict local heat loads on next-generation flight vehicles. The results at an intermediate axial section of the cone, Rex ≈ 8 × 10 5 , show three different families of spatially amplified linear global modes, the attachment-line and cross-flow modes known from earlier analyses, and a new global mode, peaking in the vicinity of the minor axis of the cone, termed "center-line mode". We discover that a sequence of symmetric and anti-symmetric centerline modes exist and, for the basic flow at hand, are maximally amplified around F * = 130 kHz. The wavenumbers and spatial distribution of amplitude functions of the centerline modes are documented.

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“…(Flow conditions: ρ ∞ = 0.03487 kg/m 3 , T ∞ = 56.7 K, and u ∞ = 1208 m/s; the cone is 24 cm in length, and Re L = 3.56 × 10 6 .) The present simulations were motivated by the experiments of Huntley and Smits, 58 and build on previous work by Bartkowicz et al 59 In that work, a spectrum of acoustic disturbances was added to the free-stream to mimic the acoustic environment of experiment. Growth of a wide variety of disturbances was observed and similar behavior of the separated symmetry plane flow was found between experiments and simulations.…”

Section: Viid Simulation Of Instability Growth On An Elliptic Conementioning

confidence: 99%

Development of the US3D Code for Advanced Compressible and Reacting Flow Simulations

Candler

Johnson²,

Nompelis³

et al. 2015

53rd AIAA Aerospace Sciences Meeting

143

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Aerothermodynamics and hypersonic flows involve complex multi-disciplinary physics, including finite-rate gas-phase kinetics, finite-rate internal energy relaxation, gas-surface interactions with finite-rate oxidation and sublimation, transition to turbulence, large-scale unsteadiness, shock-boundary layer interactions, fluid-structure interactions, and thermal protection system ablation and thermal response. Many of the flows have a large range of length and time scales, requiring large computational grids, implicit time integration, and large solution run times. The University of Minnesota / NASA US3D code was designed for the simulation of these complex, highly-coupled flows. It has many of the features of NASA's well-established DPLR code, but uses unstructured grids and has many advanced numerical capabilities and physical models for multi-physics problems. The main capabilities of the code are described, the physical modeling approaches are discussed, the different types of numerical flux functions and time integration approaches are outlined, and the parallelization strategy is overviewed. Comparisons between US3D and the NASA DPLR code are presented, along with several advanced simulations to illustrate some novel features of the code.

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Simulation of Boundary Layer Transition on Elliptic Cones in Hypersonic Flow

Cited by 16 publications

References 10 publications

Direct Numerical Simulation on the Receptivity, Instability, and Transition of Hypersonic Boundary Layers

Direct Numerical Simulation on the Receptivity, Instability, and Transition of Hypersonic Boundary Layers

Spatial linear global instability analysis of the HIFiRE-5 elliptic cone model flow

Development of the US3D Code for Advanced Compressible and Reacting Flow Simulations

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