Experimental and Computational Fluid Dynamics Study of Hayabusa Reentry Peak Heating

Fahy, Elise; Buttsworth, David; Gollan, Rowan; Jacobs, Peter A.; Morgan, Richard G.; James, Christopher M.

doi:10.2514/1.a34863

Cited by 7 publications

(2 citation statements)

References 60 publications

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“…A structured grid of 240 × 240 is used, which is similar to that used in other comparable works from the recent literature (Fahy et al 2021;Luo et al 2023;Guo, Wang & Li 2024). Strong clustering is implemented at the shock front and normal to the wall, as shown in figure 5.…”

Section: Methodsmentioning

confidence: 99%

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The influence of hypersonic free-stream conicity on the flow over a sphere

Gu,

Wen,

Hao

et al. 2024

J. Fluid Mech.

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The influence of free-stream conicity on the various aspects of the flow over a spherical test model is examined using both analytical and numerical methods. For the analytical method, a simple closed-form analytical model is assembled. Six different free-stream conditions with different Mach numbers, Reynolds numbers and thermochemistry are tested at four different degrees of conicity corresponding to those which can realistically be encountered in experiments. It is found that the results around the stagnation point are mostly insensitive to the flow condition and gas type, except for some mild non-equilibrium effects, and excellent agreement between the analytical and numerical results exists. The shock stand-off distance on the stagnation streamline is shown to decrease with increasing conicity. This decrease increases the tangential velocity gradient at the stagnation point, increasing the stagnation point heat flux and decreasing the stagnation point boundary layer thickness. The free-stream conicity is also found to alter the normalized distributions of the shock stand-off distance, heat flux, surface pressure and boundary layer thickness with the angle from the stagnation point. In general, increasing the conicity magnifies the slope of these distributions. Regarding the boundary layer transition, it is found that, if it occurs in a uniform free stream, it would also occur in a conical free stream, albeit with the transition point shifted upstream closer to the stagnation point due to the increase in the boundary layer edge tangential velocity. Overall, considering the relevant experimental uncertainties, corrections for free-stream conicity are generally recommended when larger test models are used.

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Section: Methodsmentioning

confidence: 99%

“…A structured grid of is used, which is similar to that used in other comparable works from the recent literature (Fahy et al. 2021; Luo et al. 2023; Guo, Wang & Li 2024).…”

Section: Methodsmentioning

confidence: 99%

The influence of hypersonic free-stream conicity on the flow over a sphere

Gu,

Wen,

Hao

et al. 2024

J. Fluid Mech.

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Eilmer: An open-source multi-physics hypersonic flow solver

Gibbons

Damm

Jacobs

et al. 2023

Computer Physics Communications

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Improved Surface Temperature Identification Method for Remote Observations of Sample Return Capsules

Birch,

Buttsworth,

Zander

2024

Journal of Spacecraft and Rockets

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A new method for the identification of the peak temperature of the heat shield based on remote spectral irradiance measurements is proposed and tested through the analysis of results from the Hayabusa sample return capsule. To identify the peak temperature of the heat shield, a parameterized empirical model for the surface temperature distribution on the geometry is developed, and it is then used to simulate spectra for optimized fitting with a measured spectral radiance. This new peak temperature identification method is shown to be insensitive to the wavelengths resolved, the view of the geometry, and measurement noise. The peak temperature of the Hayabusa capsule geometry at the representative condition considered (3330 K) was resolved to within 20 K for the three instruments investigated, while the effective temperature varied by around 600 K depending on which instrument was used. The error in the peak temperature model is also shown to be an order of magnitude less sensitive to measurement noise than the effective temperature approach. The new peak temperature method facilitates the direct comparison of results from instruments with different bandwidths and/or different view angles of the capsule, which was previously not possible.

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Experimental and Computational Fluid Dynamics Study of Hayabusa Reentry Peak Heating

Cited by 7 publications

References 60 publications

The influence of hypersonic free-stream conicity on the flow over a sphere

The influence of hypersonic free-stream conicity on the flow over a sphere

Eilmer: An open-source multi-physics hypersonic flow solver

Improved Surface Temperature Identification Method for Remote Observations of Sample Return Capsules

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