Numerical Assessment of Camphor Ablation Flight Relevance in Hypersonic Wind-Tunnel Testing

Rotondi, Marco; Migliorino, Mario Tindaro; Bianchi, Daniele; Pagani, Pietro; Turchi, Alessandro

doi:10.2514/1.a35318

Cited by 4 publications

(4 citation statements)

References 55 publications

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“…is considered. Vapor pressure and material properties for the Air-Camphor mixture is taken to be as in the work of Rotondi et al [13]. Steady mass blowing rates predicted by both solvers are compared in Fig.…”

Section: Base Flow With Ablative Blowingmentioning

confidence: 99%

“…These interactions are handled by their respective methodologies for both INCA and CHAMPS as discussed in Section II.B. For the solid density of camphor, a value of 990 kg m −3 is taken [13], which dictates the recession speed of the solid according to Eq. 4.…”

Section: B Perturbed Flow With Ablating Rampmentioning

confidence: 99%

“…Review articles on this past research have been compiled for studying laminar to turbulent transition [1][2][3][4] with roughness [5] as well as with ablation [6,7]. As for more recent studies from the past few years, notable contributions have been made in modeling GSI [8][9][10], performing laminar hypersonic simulations with ablation coupling [11][12][13], investigating stability and transition to turbulence in hypersonic flows [14][15][16][17][18][19] with roughness [20,21] or with blowing [22,23] and further with ablation [24][25][26][27][28], and in performing turbulent hypersonic simulations [29,30]. Moreover, there has also been a recently renewed interest for studying ablative shape change with low-temperature ablators [13,31,32] as they exhibit characteristics similar to that of real flight ablators at lower enthalpy conditions.…”

Section: Introductionmentioning

confidence: 99%

“…As for more recent studies from the past few years, notable contributions have been made in modeling GSI [8][9][10], performing laminar hypersonic simulations with ablation coupling [11][12][13], investigating stability and transition to turbulence in hypersonic flows [14][15][16][17][18][19] with roughness [20,21] or with blowing [22,23] and further with ablation [24][25][26][27][28], and in performing turbulent hypersonic simulations [29,30]. Moreover, there has also been a recently renewed interest for studying ablative shape change with low-temperature ablators [13,31,32] as they exhibit characteristics similar to that of real flight ablators at lower enthalpy conditions. There still exists large uncertainties in the predictions and interactions of various effects, and some phenomena such as transition control with roughness [20] is yet to be understood properly.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

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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Section: Base Flow With Ablative Blowingmentioning

confidence: 99%

Section: B Perturbed Flow With Ablating Rampmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Fluid Ablation Interactions on a Compression Ramp at Mach 8

Dungan,

Baskaya,

Hickel

et al. 2024

AIAA SCITECH 2024 Forum

View full text Add to dashboard Cite

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Computational Analysis and Regression Laws for Nozzle Erosion Prediction in Hybrid Rockets

Rotondi,

Migliorino,

Bianchi

et al. 2024

Journal of Propulsion and Power

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The erosion of the nozzle throat can represent one of the major limitations against the future widespread use of hybrid rocket engines (HREs) in the space industry. In fact, nozzle erosion in HREs can be more severe and harder to predict than in solid rockets due to the higher concentration of oxidizing species in the combustion products and to mixture ratio shifts and/or throttling. Therefore, an accurate understanding of the erosion phenomenon is of fundamental importance for the technological advancement of HREs. This work is focused on the investigation of graphite nozzle erosion in HREs burning high-density polyethylene with two different oxidizers, oxygen and nitrous oxide. First, the results of a computational fluid dynamics parametric analysis are used to derive closed-form regression laws for the rapid estimation of nozzle throat erosion and wall temperature depending on chamber pressure and mixture ratio. Then, a one-dimensional transient heat conduction solver is loosely coupled with the aforementioned regression laws, allowing to reconstruct the transient heating process within the solid. The obtained numerical results are validated against experimental data. Finally, the effect of gas-phase reactions on the heterogeneous reactions occurring at the nozzle surface is highlighted when moving from fuel-rich to oxidizer-rich conditions.

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