Computations of the Shock Waves at Hypersonic Velocities Taken into Account the Chemical Reactions that Appear in the Air at High Temperatures
The temperature in the nose region of a hypersonic vehicle can be extremely high, for example, reaching approximately 11 000 K at a Mach number of 36 (Apollo reentry). The bow shock wave is normal, or nearly normal, in the nose region of a blunt body, and the gas temperature behind this shock wave c...
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National Institute for Aerospace Research “Elie Carafoli” - INCAS
2015-09-01
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| Online Access: | http://bulletin.incas.ro/files/niculescu_cojocaru_pricop_pepelea_vol_7_iss_3.pdf |
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doaj-d013f88b6f064aacb564a95930d83a242020-11-24T23:44:05ZengNational Institute for Aerospace Research “Elie Carafoli” - INCASINCAS Bulletin2066-82012247-45282015-09-017312913310.13111/2066-8201.2015.7.3.12Computations of the Shock Waves at Hypersonic Velocities Taken into Account the Chemical Reactions that Appear in the Air at High TemperaturesMihai Leonida NICULESCU0Marius Gabriel COJOCARU1Mihai Victor PRICOP2Dumitru PEPELEA3INCAS − National Institute for Aerospace Research “Elie Carafoli”, Flow Physics Department, Numerical Simulation Unit, B-dul Iuliu Maniu 220, Bucharest 061126, Romania niculescu.mihai@incas.ro*INCAS − National Institute for Aerospace Research “Elie Carafoli”, Flow Physics Department, Numerical Simulation Unit, B-dul Iuliu Maniu 220, Bucharest 061126, Romania, cojocaru.gabriel@incas.roINCAS − National Institute for Aerospace Research “Elie Carafoli”, Flow Physics Department, Numerical Simulation Unit, B-dul Iuliu Maniu 220, Bucharest 061126, Romania, pricop.victor@incas.roINCAS − National Institute for Aerospace Research “Elie Carafoli”, Flow Physics Department, Numerical Simulation Unit, B-dul Iuliu Maniu 220, Bucharest 061126, Romania, pepelea.dumitru@incas.roThe temperature in the nose region of a hypersonic vehicle can be extremely high, for example, reaching approximately 11 000 K at a Mach number of 36 (Apollo reentry). The bow shock wave is normal, or nearly normal, in the nose region of a blunt body, and the gas temperature behind this shock wave can be enormous at hypersonic speeds. In this case, the assumption of a calorically perfect nonreacting gas with the ratio of specific heats of 1.4 gives an unrealistically high value of temperature. Therefore, the proper inclusion of chemically reacting effects is vital to the calculation of an accurate normal shock wave temperature.http://bulletin.incas.ro/files/niculescu_cojocaru_pricop_pepelea_vol_7_iss_3.pdfHypersonic flowshock waveschemical reactionsCFDcapsule reentry |
| collection |
DOAJ |
| language |
English |
| format |
Article |
| sources |
DOAJ |
| author |
Mihai Leonida NICULESCU Marius Gabriel COJOCARU Mihai Victor PRICOP Dumitru PEPELEA |
| spellingShingle |
Mihai Leonida NICULESCU Marius Gabriel COJOCARU Mihai Victor PRICOP Dumitru PEPELEA Computations of the Shock Waves at Hypersonic Velocities Taken into Account the Chemical Reactions that Appear in the Air at High Temperatures INCAS Bulletin Hypersonic flow shock waves chemical reactions CFD capsule reentry |
| author_facet |
Mihai Leonida NICULESCU Marius Gabriel COJOCARU Mihai Victor PRICOP Dumitru PEPELEA |
| author_sort |
Mihai Leonida NICULESCU |
| title |
Computations of the Shock Waves at Hypersonic Velocities Taken into Account the Chemical Reactions that Appear in the Air at High Temperatures |
| title_short |
Computations of the Shock Waves at Hypersonic Velocities Taken into Account the Chemical Reactions that Appear in the Air at High Temperatures |
| title_full |
Computations of the Shock Waves at Hypersonic Velocities Taken into Account the Chemical Reactions that Appear in the Air at High Temperatures |
| title_fullStr |
Computations of the Shock Waves at Hypersonic Velocities Taken into Account the Chemical Reactions that Appear in the Air at High Temperatures |
| title_full_unstemmed |
Computations of the Shock Waves at Hypersonic Velocities Taken into Account the Chemical Reactions that Appear in the Air at High Temperatures |
| title_sort |
computations of the shock waves at hypersonic velocities taken into account the chemical reactions that appear in the air at high temperatures |
| publisher |
National Institute for Aerospace Research “Elie Carafoli” - INCAS |
| series |
INCAS Bulletin |
| issn |
2066-8201 2247-4528 |
| publishDate |
2015-09-01 |
| description |
The temperature in the nose region of a hypersonic vehicle can be extremely high, for example, reaching approximately 11 000 K at a Mach number of 36 (Apollo reentry). The bow shock wave is normal, or nearly normal, in the nose region of a blunt body, and the gas temperature behind this shock wave can be enormous at hypersonic speeds. In this case, the assumption of a calorically perfect nonreacting gas with the ratio of specific heats of 1.4 gives an unrealistically high value of temperature. Therefore, the proper inclusion of chemically reacting effects is vital to the calculation of an accurate normal shock wave temperature. |
| topic |
Hypersonic flow shock waves chemical reactions CFD capsule reentry |
| url |
http://bulletin.incas.ro/files/niculescu_cojocaru_pricop_pepelea_vol_7_iss_3.pdf |
| work_keys_str_mv |
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1725500129047216128 |