Numerical Investigation of Fluid-Ablation Interactions for a Mach 5.3 Transitional Boundary Layer Flow Over a 13 Degree Cone

Dungan, Sean D.; Brehm, Christoph; McQuaid, Joel A.; Zibitsker, Aleksander L.; Martin, Alexandre

doi:10.2514/6.2023-0476

Cited by 3 publications

(2 citation statements)

References 27 publications

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“…Rogers et al [10] used a conjugate heat transfer and gas-solid surface interaction model to study the ablation process of reentry vehicles and the influence of head bluntness on boundary layer stability during ablation and found that head bluntness had a strong destabilizing effect on the upstream boundary layer while the stability of the downstream boundary layer remained unaffected. Dungan et al [11] employed direct numerical simulation (DNS) to investigate the interaction between the flow field and ablation in transitional boundary layers. Meng et al [12] used a fluid-thermal-ablation coupled approach to calculate the ablation of a cone-shaped vehicle.…”

Section: Introductionmentioning

confidence: 99%

Fluid-solid-ablation coupled calculation of hypersonic vehicle based on rbf grid deformation method

Yang,

Dai,

Zhao

et al. 2024

J. Phys.: Conf. Ser.

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The ablative phenomenon of the thermal protection system happens when the hypersonic vehicle suffers serious challenges of aerothermal due to high Mach number. To determine whether the thermal protection system is destroyed, the fluid-solid-ablation loosely coupled method for Carbon-Carbon composite materials is proposed to calculate the deformation of ablation and acquire the deformed shape. Navier-Stokes equation, heat conduction equation, and linear ablation model are applied to calculate the fluid field, the solid field, and the ablation receding amount. As one of the most widely applicable dynamic mesh methods, the Radial Basis Functions (RBF) dynamic method is used to get the deformed solid mesh. The ablation of a missile is computed and analyzed. It could be found that the surface temperature of the head increases during flight and the ablation of the surface results in the change of the vehicle’s shape. The ablative layer thickness of the thermal protection system should be greater than the max ablative deformation, reaching 4.4 mm of the missile. The proposed fluid-solid coupling method could effectively predict the ablation deformation of the vehicle and guide the design of hypersonic vehicle thermal protection systems.

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Section: Introductionmentioning

confidence: 99%

Fluid-solid-ablation coupled calculation of hypersonic vehicle based on rbf grid deformation method

Yang,

Dai,

Zhao

et al. 2024

J. Phys.: Conf. Ser.

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“…Moving boundary ablation simulations showed considerable generation of vorticity over the camphor surface, however, ablation affecting specific boundary layer instability modes was not an objective of that research and, therefore, was not investigated. The same year, Dungan et al [36] investigated camphor FAI over a straight cone at Mach 5.3. Using a loose coupling approach with curvilinear meshes and one-dimensional ray material response solvers, the authors showed only minor destabilization of first mode disturbances due to ablation.…”

Section: Introductionmentioning

confidence: 99%

Fluid Ablation Interactions on a Compression Ramp at Mach 8

Dungan,

Baskaya,

Hickel

et al. 2024

AIAA SCITECH 2024 Forum

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Direct numerical simulations (DNS) are performed over a 15°compression ramp undergoing ablation at Mach 8 to examine fluid-ablation interactions (FAI) on transitional high-speed boundary layers. The experiments at these conditions with a rigid wall are first numerically replicated for a laminar flow. Heating streaks are introduced by introducing perturbations in the baseflow informed by prior stability calculations. The ramp is then replaced by a low-temperature ablator in our DNS and the interaction of the streaks with the recessing ablator surface are examined. Different approaches from two independently developed solvers are used to study this problem. Overall, both solvers provide qualitatively and quantitatively very similar results; however, differences in streak amplification and mass blowing magnitudes are observed. We discuss the difficulties in accurately predicting ablation and present the first findings regarding its influence on the perturbation evolution and transition to turbulence for this configuration.

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Hypersonic Fluid-Thermal-Structural Interactions on a Compression Ramp with an Embedded Compliant Panel

Schöneich

Laurence

Dettenrieder

et al. 2023

AIAA AVIATION 2023 Forum

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Numerical Investigation of Fluid-Ablation Interactions for a Mach 5.3 Transitional Boundary Layer Flow Over a 13 Degree Cone

Cited by 3 publications

References 27 publications

Fluid-solid-ablation coupled calculation of hypersonic vehicle based on rbf grid deformation method

Fluid-solid-ablation coupled calculation of hypersonic vehicle based on rbf grid deformation method

Fluid Ablation Interactions on a Compression Ramp at Mach 8

Hypersonic Fluid-Thermal-Structural Interactions on a Compression Ramp with an Embedded Compliant Panel

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