Physico-Mathematical Modeling of the Advanced Active Thermal Protection Method for High-Speed Aerospace Vehicle Structures.
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| Title: | Physico-Mathematical Modeling of the Advanced Active Thermal Protection Method for High-Speed Aerospace Vehicle Structures. |
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| Authors: | Formalev, V. F.1 (AUTHOR) formalev38@yandex.ru, Kolesnik, S. A.1 (AUTHOR) sergey@oviont.com, Garibyan, B. A.1 (AUTHOR) bagarib@yandex.ru |
| Source: | Technical Physics Letters. Jul2025, Vol. 51 Issue 7, p271-277. 7p. |
| Subjects: | Dynamic viscosity, Coolants, Thermal boundary layer, Heat flux, Thermal shielding, Numerical calculations, Liquid films, High-speed aeronautics |
| Abstract: | A new method is proposed for thermal protection of high-speed aircraft (HSA) nose cones, which is based on injection of a coolant with a strong temperature dependence of its dynamic viscosity (changing by 3‒5 orders of magnitude upon temperatures variation from 300 to 500 K) into the gas-dynamic boundary layer. This dependence allows the design of an automatic system for coolant delivery through channels formed in the structure onto the blunt cone surface, since, as the temperature of the structure increases, the coolant viscosity drops sharply, its fluidity increases, and, at a constant pressure differential between the coolant reservoir and the surface, its delivery to the boundary layer increases, forming a protective liquid film that flows and evaporates, injecting vapor into the boundary layer. As the structural temperature drops, the coolant delivery decreases. The efficiency of this thermal protection method is related to the fact that, first, the HSA surface temperature does not exceed the coolant evaporation temperature and, second, the HSA structure operates without mass loss and maintains its geometry. Numerical results have been obtained for the mass flow rate, mass evaporation rate of the liquid coolant film, its temperature, and the HSA structure temperature. [ABSTRACT FROM AUTHOR] |
| Copyright of Technical Physics Letters is the property of Springer Nature and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) | |
| Database: | Engineering Source |
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| Header | DbId: egs DbLabel: Engineering Source An: 190358324 AccessLevel: 6 PubType: Academic Journal PubTypeId: academicJournal PreciseRelevancyScore: 0 |
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| Items | – Name: Title Label: Title Group: Ti Data: Physico-Mathematical Modeling of the Advanced Active Thermal Protection Method for High-Speed Aerospace Vehicle Structures. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22Formalev%2C+V%2E+F%2E%22">Formalev, V. F.</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> formalev38@yandex.ru</i><br /><searchLink fieldCode="AR" term="%22Kolesnik%2C+S%2E+A%2E%22">Kolesnik, S. A.</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> sergey@oviont.com</i><br /><searchLink fieldCode="AR" term="%22Garibyan%2C+B%2E+A%2E%22">Garibyan, B. A.</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> bagarib@yandex.ru</i> – Name: TitleSource Label: Source Group: Src Data: <searchLink fieldCode="JN" term="%22Technical+Physics+Letters%22">Technical Physics Letters</searchLink>. Jul2025, Vol. 51 Issue 7, p271-277. 7p. – Name: Subject Label: Subjects Group: Su Data: <searchLink fieldCode="DE" term="%22Dynamic+viscosity%22">Dynamic viscosity</searchLink><br /><searchLink fieldCode="DE" term="%22Coolants%22">Coolants</searchLink><br /><searchLink fieldCode="DE" term="%22Thermal+boundary+layer%22">Thermal boundary layer</searchLink><br /><searchLink fieldCode="DE" term="%22Heat+flux%22">Heat flux</searchLink><br /><searchLink fieldCode="DE" term="%22Thermal+shielding%22">Thermal shielding</searchLink><br /><searchLink fieldCode="DE" term="%22Numerical+calculations%22">Numerical calculations</searchLink><br /><searchLink fieldCode="DE" term="%22Liquid+films%22">Liquid films</searchLink><br /><searchLink fieldCode="DE" term="%22High-speed+aeronautics%22">High-speed aeronautics</searchLink> – Name: Abstract Label: Abstract Group: Ab Data: A new method is proposed for thermal protection of high-speed aircraft (HSA) nose cones, which is based on injection of a coolant with a strong temperature dependence of its dynamic viscosity (changing by 3‒5 orders of magnitude upon temperatures variation from 300 to 500 K) into the gas-dynamic boundary layer. This dependence allows the design of an automatic system for coolant delivery through channels formed in the structure onto the blunt cone surface, since, as the temperature of the structure increases, the coolant viscosity drops sharply, its fluidity increases, and, at a constant pressure differential between the coolant reservoir and the surface, its delivery to the boundary layer increases, forming a protective liquid film that flows and evaporates, injecting vapor into the boundary layer. As the structural temperature drops, the coolant delivery decreases. The efficiency of this thermal protection method is related to the fact that, first, the HSA surface temperature does not exceed the coolant evaporation temperature and, second, the HSA structure operates without mass loss and maintains its geometry. Numerical results have been obtained for the mass flow rate, mass evaporation rate of the liquid coolant film, its temperature, and the HSA structure temperature. [ABSTRACT FROM AUTHOR] – Name: AbstractSuppliedCopyright Label: Group: Ab Data: <i>Copyright of Technical Physics Letters is the property of Springer Nature and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.) |
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| RecordInfo | BibRecord: BibEntity: Identifiers: – Type: doi Value: 10.1134/S106378502560070X Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 7 StartPage: 271 Subjects: – SubjectFull: Dynamic viscosity Type: general – SubjectFull: Coolants Type: general – SubjectFull: Thermal boundary layer Type: general – SubjectFull: Heat flux Type: general – SubjectFull: Thermal shielding Type: general – SubjectFull: Numerical calculations Type: general – SubjectFull: Liquid films Type: general – SubjectFull: High-speed aeronautics Type: general Titles: – TitleFull: Physico-Mathematical Modeling of the Advanced Active Thermal Protection Method for High-Speed Aerospace Vehicle Structures. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: Formalev, V. F. – PersonEntity: Name: NameFull: Kolesnik, S. A. – PersonEntity: Name: NameFull: Garibyan, B. A. IsPartOfRelationships: – BibEntity: Dates: – D: 01 M: 07 Text: Jul2025 Type: published Y: 2025 Identifiers: – Type: issn-print Value: 10637850 Numbering: – Type: volume Value: 51 – Type: issue Value: 7 Titles: – TitleFull: Technical Physics Letters Type: main |
| ResultId | 1 |
