Mathematical Modeling of Aerodynamic Heating and Pressure Distribution on a 5-Inch Hemispherical Concave Nose in Supersonic Flow
During the design of an aircraft, a significant parameter that is taken into consideration is aerodynamic heating. Aerodynamically induced heating affects both the structure of the aircraft and its vulnerability to heat-seeking missiles in modern warfare. As a result, the ability to calculate effici...
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| Autores principales: | , , |
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| Formato: | Capítulo de libro |
| Lenguaje: | inglés |
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IntechOpen
2020
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| Acceso en línea: | https://www.intechopen.com/chapters/71086 |
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| _version_ | 1879164694212640769 |
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| author | Spiridakos, Dimitrios P. Markatos, Nicholas C. Karadimou, Despoina |
| author_browse | Karadimou, Despoina Markatos, Nicholas C. Spiridakos, Dimitrios P. |
| author_facet | Spiridakos, Dimitrios P. Markatos, Nicholas C. Karadimou, Despoina |
| author_sort | Spiridakos, Dimitrios P. |
| building | IntechOpen |
| collection | Acceso abierto |
| description | During the design of an aircraft, a significant parameter that is taken into consideration is aerodynamic heating. Aerodynamically induced heating affects both the structure of the aircraft and its vulnerability to heat-seeking missiles in modern warfare. As a result, the ability to calculate efficiently the heating produced as well as the pressure distribution in such flows is crucial. Therefore, in this present study, the PHOENICS CFD code as modified by DRA Farnborough in order to calculate heat transfer and pressure measurement on a 5-inch hemispherical concave nose at a Mach number of 2.0 is evaluated and customized in order to produce faster and more accurate results. Apart from numerical alterations, different turbulence models are being examined as well as different discretization schemes. Numerical solutions show improvement up to 6% in comparison with the original model, both in terms of convergence rate and in terms of agreement with the available experimental data. With the new modeling suggested in the present work, the significance of both the discretization scheme and the choice of the turbulence modeling is demonstrated for the flows under consideration. The use of a high-order discretization scheme is suggested for more acute areas of the body modeled in order to improve results further. |
| doi_str_mv | 10.5772/intechopen.91041 |
| first_indexed | 2026-10-15T21:38:24Z |
| format | Book Chapter |
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<dc:title>Mathematical Modeling of Aerodynamic Heating and Pressure Distribution on a 5-Inch Hemispherical Concave Nose in Supersonic Flow</dc:title>
<dc:creator>Dimitrios P. Spiridakos</dc:creator>
<dc:creator>Nicholas C. Markatos</dc:creator>
<dc:creator>Despoina Karadimou</dc:creator>
<dc:subject>Physical Sciences, Engineering and Technology</dc:subject>
<dc:description>During the design of an aircraft, a significant parameter that is taken into consideration is aerodynamic heating. Aerodynamically induced heating affects both the structure of the aircraft and its vulnerability to heat-seeking missiles in modern warfare. As a result, the ability to calculate efficiently the heating produced as well as the pressure distribution in such flows is crucial. Therefore, in this present study, the PHOENICS CFD code as modified by DRA Farnborough in order to calculate heat transfer and pressure measurement on a 5-inch hemispherical concave nose at a Mach number of 2.0 is evaluated and customized in order to produce faster and more accurate results. Apart from numerical alterations, different turbulence models are being examined as well as different discretization schemes. Numerical solutions show improvement up to 6% in comparison with the original model, both in terms of convergence rate and in terms of agreement with the available experimental data. With the new modeling suggested in the present work, the significance of both the discretization scheme and the choice of the turbulence modeling is demonstrated for the flows under consideration. The use of a high-order discretization scheme is suggested for more acute areas of the body modeled in order to improve results further.</dc:description>
<dc:publisher>IntechOpen</dc:publisher>
<dc:date>2020-02-12</dc:date>
<dc:type>Chapter, Part Of Book</dc:type>
<dc:identifier>https://www.intechopen.com/chapters/71086</dc:identifier>
<dc:identifier>doi:10.5772/intechopen.91041</dc:identifier>
<dc:language>en</dc:language>
<dc:relation>ISBN:978-1-78923-869-3</dc:relation>
<dc:rights>https://creativecommons.org/licenses/by/3.0/</dc:rights>
<dc:source>https://www.intechopen.com/books/7678 ; Computational Models in Engineering</dc:source>
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| id | intech-71086 |
| institution | IntechOpen |
| isbn | 978-1-78923-869-3 |
| language | English |
| last_indexed | 2026-10-15T21:38:24Z |
| publishDate | 2020 |
| publishDateRange | 2020 |
| publishDateSort | 2020 |
| publisher | IntechOpen |
| publisherStr | IntechOpen |
| record_format | oai_dc |
| spelling | intech-710862020-02-12 Mathematical Modeling of Aerodynamic Heating and Pressure Distribution on a 5-Inch Hemispherical Concave Nose in Supersonic Flow Dimitrios P. Spiridakos Nicholas C. Markatos Despoina Karadimou Physical Sciences, Engineering and Technology During the design of an aircraft, a significant parameter that is taken into consideration is aerodynamic heating. Aerodynamically induced heating affects both the structure of the aircraft and its vulnerability to heat-seeking missiles in modern warfare. As a result, the ability to calculate efficiently the heating produced as well as the pressure distribution in such flows is crucial. Therefore, in this present study, the PHOENICS CFD code as modified by DRA Farnborough in order to calculate heat transfer and pressure measurement on a 5-inch hemispherical concave nose at a Mach number of 2.0 is evaluated and customized in order to produce faster and more accurate results. Apart from numerical alterations, different turbulence models are being examined as well as different discretization schemes. Numerical solutions show improvement up to 6% in comparison with the original model, both in terms of convergence rate and in terms of agreement with the available experimental data. With the new modeling suggested in the present work, the significance of both the discretization scheme and the choice of the turbulence modeling is demonstrated for the flows under consideration. The use of a high-order discretization scheme is suggested for more acute areas of the body modeled in order to improve results further. IntechOpen 2020-02-12 Chapter, Part Of Book https://www.intechopen.com/chapters/71086 doi:10.5772/intechopen.91041 en ISBN:978-1-78923-869-3 https://creativecommons.org/licenses/by/3.0/ https://www.intechopen.com/books/7678 ; Computational Models in Engineering |
| spellingShingle | Physical Sciences, Engineering and Technology Spiridakos, Dimitrios P. Markatos, Nicholas C. Karadimou, Despoina Mathematical Modeling of Aerodynamic Heating and Pressure Distribution on a 5-Inch Hemispherical Concave Nose in Supersonic Flow |
| title | Mathematical Modeling of Aerodynamic Heating and Pressure Distribution on a 5-Inch Hemispherical Concave Nose in Supersonic Flow |
| title_full | Mathematical Modeling of Aerodynamic Heating and Pressure Distribution on a 5-Inch Hemispherical Concave Nose in Supersonic Flow |
| title_fullStr | Mathematical Modeling of Aerodynamic Heating and Pressure Distribution on a 5-Inch Hemispherical Concave Nose in Supersonic Flow |
| title_full_unstemmed | Mathematical Modeling of Aerodynamic Heating and Pressure Distribution on a 5-Inch Hemispherical Concave Nose in Supersonic Flow |
| title_short | Mathematical Modeling of Aerodynamic Heating and Pressure Distribution on a 5-Inch Hemispherical Concave Nose in Supersonic Flow |
| title_sort | mathematical modeling of aerodynamic heating and pressure distribution on a 5 inch hemispherical concave nose in supersonic flow |
| topic | Physical Sciences, Engineering and Technology |
| url | https://www.intechopen.com/chapters/71086 |
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