Aerodynamic analysis of a scramjet for atmospheric flight
This paper presents an aerodynamic conception of an academic scramjet designed for a flight at 6.2 km of altitude with a speed corresponding to Mach number 4.18, which will be coupled to the intermediate training rocket (FTI) of the Barreira do Inferno Launch Center (CLBI) in Rio Grande do Norte (RN...
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| Formato: | bachelorThesis |
| Idioma: | English English |
| Publicado em: |
Universidade Federal do Rio Grande do Norte
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| Endereço do item: | https://repositorio.ufrn.br/handle/123456789/43070 |
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| Resumo: | This paper presents an aerodynamic conception of an academic scramjet designed for a flight at 6.2 km of altitude with a speed corresponding to Mach number 4.18, which will be coupled to the intermediate training rocket (FTI) of the Barreira do Inferno Launch Center (CLBI) in Rio Grande do Norte (RN), Brazil. The current means of access to space is limited by the quantity of fuel that rockets need to take to get out of the dense layers of the atmosphere, which causes little payload to be boarded, limiting aerospace activities. The scramjet technological demonstrator is being studied as a new technology of access to space, as this technology proposes a new system of airbreathing propulsion. The proposed academic scramjet will be coupled in the FTI, functioning as a second stage in order to obtain more power during the flight. Calculations were made in the geometry variation in order to select the best compression and expansion section for the scramjet, with heat addition. In the compression section, only one configuration with three tamps was considered. The analytical results were compared with simulation results. |
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