Nonablative Dual-Jet Strategy for Drag and Heat Reduction of Hypersonic Blunt Vehicles

Zhu, Liang; Tian, Xiaotao; Li, Weixuan; Yan, Mi; Xiang, Tang; Huang, Meng

doi:10.1061/(asce)as.1943-5525.0001290

Cited by 5 publications

(2 citation statements)

References 64 publications

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“…Particularly, in the aerospike cases, the predicted heat flux peaks appear earlier in the hemispherical body surface and seem higher and more sharp. A similar phenomena can also be found in references [ 32 , 33 ], and the deviations can be attributed to the assumption of a uniform wall temperature and experimental errors. In fact, it was argued in the original report [ 5 ] that “In the aerospike case, the heat flux distribution curve has a more-rounded peak than expected because of the estimated data around the peak in that case.…”

Section: Numerical Results and Discussionsupporting

confidence: 79%

Application of a Gas-Kinetic BGK Scheme in Thermal Protection System Analysis for Hypersonic Vehicles

Zhou

Guo

et al. 2022

Entropy

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One major problem in the development of hypersonic vehicles is severe aerodynamic heating; thus, the implementation of a thermal protection system is required. A numerical investigation on the reduction of aerodynamic heating using different thermal protection systems is conducted using a novel gas-kinetic BGK scheme. This method adopts a different solution strategy from the conventional computational fluid dynamics technique, and has shown a lot of benefits in the simulation of hypersonic flows. To be specific, it is established based on solving the Boltzmann equation, and the obtained gas distribution function is used to reconstruct the macroscopic solution of the flow field. Within the finite volume framework, the present BGK scheme is specially designed for the evaluation of numerical fluxes across the cell interface. Two typical thermal protection systems are investigated by using spikes and opposing jets, separately. Both their effectiveness and mechanisms to protect the body surface from heating are analyzed. The predicted distributions of pressure and heat flux, and the unique flow characteristics brought by spikes of different shapes or opposing jets of different total pressure ratios all verify the reliability and accuracy of the BGK scheme in the thermal protection system analysis.

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Section: Numerical Results and Discussionsupporting

confidence: 79%

Application of a Gas-Kinetic BGK Scheme in Thermal Protection System Analysis for Hypersonic Vehicles

Zhou

Guo

et al. 2022

Entropy

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“…The authors of [51,52] proposed and validated a design that combined an opposing jet, a lateral jet, and the aerospike altogether. The authors from [53] innovatively placed an additional jet on the back of an aerodome, which is on the tip of an Aerospike and has already an opposing jet. The additional rearward jet helps to reduce the peak heat flux on the spike and the main body caused by the flow reattachment.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on the Thermal Protection Characteristics of a New Active Jet Design Parameter for Hypersonic Flight Vehicle

Tian

Duan

Chen

2023

International Journal of Aerospace Engineering

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This study investigated the thermal protection performance of an active jet thermal protection system (PRsAJ-TPS) based on a new jet design parameter PRs for hypersonic flight vehicles (HFVs). The new parameter PRs is defined as the relationship between the jet flow total pressure and the free flow total pressure behind the outer bow shock. A 20° tilted nozzle design is employed together with the PRs to form the PRsAJ-TPS. Theoretical and numerical analysis is performed to prove the advantages of using the PRs. A conventional in-house CFD solver with the k ‐ ω SST turbulence model is utilized to perform the calculation. The influence of different PRs (working in the short penetration mode) and flight angles of attack on the performance of the PRsAJ-TPS is also studied. The simulation results confirmed that with a constant PRs, the Mach disk location stays the same and the normalized heat flux reduction is similar at different flight conditions. Nearly linear relationships exist between the new design parameter PRs and thermal protection performance indicators. The PRsAJ-TPS also exhibits good protection when flight angle of attack (AoA) varies between 0° and 40°, with the best results achieved at AoA = 0 ° . This study provides valuable information for the engineering application of the jet-based TPS to future HFVs.

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Hypersonic drag and heat reduction mechanism of a new hybrid method of spike, multi-row discs and opposing jets aerodynamic configuration

Vali

Abbasi

2022

International Journal of Heat and Mass Transfer

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Nonablative Dual-Jet Strategy for Drag and Heat Reduction of Hypersonic Blunt Vehicles

Cited by 5 publications

References 64 publications

Application of a Gas-Kinetic BGK Scheme in Thermal Protection System Analysis for Hypersonic Vehicles

Application of a Gas-Kinetic BGK Scheme in Thermal Protection System Analysis for Hypersonic Vehicles

Numerical Investigation on the Thermal Protection Characteristics of a New Active Jet Design Parameter for Hypersonic Flight Vehicle

Hypersonic drag and heat reduction mechanism of a new hybrid method of spike, multi-row discs and opposing jets aerodynamic configuration

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