Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles
Numerical simulations are carried out to study the effect of divergence angle and adverse pressure gradient on the movement of shock wave train in a scramjet isolator. The commercial software tool ANSYS Fluent 16 was used to simplify two dimensional Reynolds averaged Navier Stokes equation with comp...
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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/72221 |
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| _version_ | 1879164725989736448 |
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| author | Gugulothu, Santhosh Kumar Bhaskar, B. Babu, V.V. Phani |
| author_browse | Babu, V.V. Phani Bhaskar, B. Gugulothu, Santhosh Kumar |
| author_facet | Gugulothu, Santhosh Kumar Bhaskar, B. Babu, V.V. Phani |
| author_sort | Gugulothu, Santhosh Kumar |
| building | IntechOpen |
| collection | Acceso abierto |
| description | Numerical simulations are carried out to study the effect of divergence angle and adverse pressure gradient on the movement of shock wave train in a scramjet isolator. The commercial software tool ANSYS Fluent 16 was used to simplify two dimensional Reynolds averaged Navier Stokes equation with compressible fluid flow by considering the density-based solver with standard K-ε turbulence model. The species transport model with single step volumetric reaction mechanism is employed. Initially, the simulated results are validated with experimental results available in open literature. The obtained results show that the variation of the divergence angle and back pressure on the scramjet isolator has greater significance on the flow field. Also, with an increase in the back pressure, due to the intense turbulent combustion, the shock wave train developed should expand along the length and also moves towards the leading edge of the isolator leading to rapid rise in the pressure so that the pressure at the entrance of the isolator can match the enhanced back pressures. |
| doi_str_mv | 10.5772/intechopen.92555 |
| first_indexed | 2026-10-15T21:38:54Z |
| format | Book Chapter |
| fullrecord | <oai_dc:dc xmlns:oai_dc="http://www.openarchives.org/OAI/2.0/oai_dc/" xmlns:dc="http://purl.org/dc/elements/1.1/" xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xsi:schemaLocation="http://www.openarchives.org/OAI/2.0/oai_dc/ http://www.openarchives.org/OAI/2.0/oai_dc.xsd"><identifier>intech-72221</identifier><datestamp>2020-05-18</datestamp>
<dc:title>Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles</dc:title>
<dc:creator>Santhosh Kumar Gugulothu</dc:creator>
<dc:creator>B. Bhaskar</dc:creator>
<dc:creator>V.V. Phani Babu</dc:creator>
<dc:subject>Physical Sciences, Engineering and Technology</dc:subject>
<dc:description>Numerical simulations are carried out to study the effect of divergence angle and adverse pressure gradient on the movement of shock wave train in a scramjet isolator. The commercial software tool ANSYS Fluent 16 was used to simplify two dimensional Reynolds averaged Navier Stokes equation with compressible fluid flow by considering the density-based solver with standard K-ε turbulence model. The species transport model with single step volumetric reaction mechanism is employed. Initially, the simulated results are validated with experimental results available in open literature. The obtained results show that the variation of the divergence angle and back pressure on the scramjet isolator has greater significance on the flow field. Also, with an increase in the back pressure, due to the intense turbulent combustion, the shock wave train developed should expand along the length and also moves towards the leading edge of the isolator leading to rapid rise in the pressure so that the pressure at the entrance of the isolator can match the enhanced back pressures.</dc:description>
<dc:publisher>IntechOpen</dc:publisher>
<dc:date>2020-05-18</dc:date>
<dc:type>Chapter, Part Of Book</dc:type>
<dc:identifier>https://www.intechopen.com/chapters/72221</dc:identifier>
<dc:identifier>doi:10.5772/intechopen.92555</dc:identifier>
<dc:language>en</dc:language>
<dc:relation>ISBN:978-1-83968-032-8</dc:relation>
<dc:rights>https://creativecommons.org/licenses/by/3.0/</dc:rights>
<dc:source>https://www.intechopen.com/books/10025 ; Numerical and Experimental Studies on Combustion Engines and Vehicles</dc:source>
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| id | intech-72221 |
| institution | IntechOpen |
| isbn | 978-1-83968-032-8 |
| language | English |
| last_indexed | 2026-10-15T21:38:54Z |
| publishDate | 2020 |
| publishDateRange | 2020 |
| publishDateSort | 2020 |
| publisher | IntechOpen |
| publisherStr | IntechOpen |
| record_format | oai_dc |
| spelling | intech-722212020-05-18 Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles Santhosh Kumar Gugulothu B. Bhaskar V.V. Phani Babu Physical Sciences, Engineering and Technology Numerical simulations are carried out to study the effect of divergence angle and adverse pressure gradient on the movement of shock wave train in a scramjet isolator. The commercial software tool ANSYS Fluent 16 was used to simplify two dimensional Reynolds averaged Navier Stokes equation with compressible fluid flow by considering the density-based solver with standard K-ε turbulence model. The species transport model with single step volumetric reaction mechanism is employed. Initially, the simulated results are validated with experimental results available in open literature. The obtained results show that the variation of the divergence angle and back pressure on the scramjet isolator has greater significance on the flow field. Also, with an increase in the back pressure, due to the intense turbulent combustion, the shock wave train developed should expand along the length and also moves towards the leading edge of the isolator leading to rapid rise in the pressure so that the pressure at the entrance of the isolator can match the enhanced back pressures. IntechOpen 2020-05-18 Chapter, Part Of Book https://www.intechopen.com/chapters/72221 doi:10.5772/intechopen.92555 en ISBN:978-1-83968-032-8 https://creativecommons.org/licenses/by/3.0/ https://www.intechopen.com/books/10025 ; Numerical and Experimental Studies on Combustion Engines and Vehicles |
| spellingShingle | Physical Sciences, Engineering and Technology Gugulothu, Santhosh Kumar Bhaskar, B. Babu, V.V. Phani Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles |
| title | Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles |
| title_full | Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles |
| title_fullStr | Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles |
| title_full_unstemmed | Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles |
| title_short | Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles |
| title_sort | numerical investigation of the shock train in a scramjet with the effects of back pressure and divergent angles |
| topic | Physical Sciences, Engineering and Technology |
| url | https://www.intechopen.com/chapters/72221 |
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