Relevant bibliographies by topics / Scramjet (motor)

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Conference papers

Academic literature on the topic 'Scramjet (motor)'

Author: Grafiati
Published: 11 September 2021
Last updated: 4 February 2022

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Journal articles on the topic "Scramjet (motor)"

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Guimarães, Jefte Da Silva, Marco Antonio Sala Minucci, and Dermeval Carinhana Júnior. "ESTUDO DE UMA CÂMARA DE COMBUSTÃO SUPERSÔNICA USANDO UM TÚNEL DE CHOQUE." CIMATech 1, no. 7 (December 23, 2020): 126–36. http://dx.doi.org/10.37619/issn2447-5378.v7i1.297.126-136.

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Túneis de Choque são dispositivos capazes de gerar escoamentos de altas temperaturas e velocidades supersônicas, simulando as condições reais de escoamento na entrada de um combustor de motor Scramjet, viabilizando o estudo de combustão supersônica. Neste trabalho, são realizados ensaios aerotermodinâmicos e de combustão supersônica utilizando um Túnel de Choque, de modo a reproduzir as condições de escoamento na entrada de um combustor de motor Scramjet. O arranjo experimental consistiu na utilização do Túnel de Choque, um dispositivo com uma seção de alta pressão (Driver) e uma seção de baixa pressão (Driven), separadas entre si por um diafragma. Ao ser rompido o diafragma, ocorre a propagação do escoamento, o qual é acelerado a velocidades supersônicas através de um bocal bidimensional conectado à câmara de combustão supersônica. A metodologia adotada possibilitou a análise do escoamento no interior da câmara de combustão supersônica do motor Scramjet, gerando escoamentos de M=2.7.
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2

Rodriguez, Carlos G. "Computational Fluid Dynamics Analysis of the Central Institute of Aviation Motors/NASA Scramjet." Journal of Propulsion and Power 19, no. 4 (July 2003): 547–55. http://dx.doi.org/10.2514/2.6165.

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Dissertations / Theses on the topic "Scramjet (motor)"

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Rodrigues, Luís. "Thermodynamic analysis and optimization of a scramjet engine with thermal management system." Master's thesis, 2010. http://hdl.handle.net/10400.6/3686.

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Thermal management of the scramjet engine is one of the key issues of the challenges brought by the development of hypersonic airbreathing vehicles. A Closed Brayton Cycle thermal management system for a regenerative cooled scramjet is introduced with the goal of reducing the hydrogen fuel flow for cooling. Part of the heat absorbed from fuel is converted into other forms of energy to decrease the heat that must be taken away by hydrogen fuel. Reducing this heat increases the fuel heat sink (cooling capacity) without requiring excess fuel for cooling and eliminating the need to search for a new coolant. The proposed thermal cycle reduces the fuel flow for cooling, and this way, the fuel on board assures the cooling requirements for the whole hypersonic vehicle. The basic concept and working principle are introduced: a thermodynamic cycle analysis is performed to demonstrate the system performance gains of Closed Brayton Cycle (CBC) Thermal Management System (TMS) over the conventional system with regenerative cooling. It was shown that the Closed Brayton Cycle Thermal Management Systems presents a high performance gain when compared to conventional regenerative cooling due to the reduction of fuel flow for cooling and additional power output.
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Books on the topic "Scramjet (motor)"

1

The scramjet engine: Processes and characteristics. Cambridge: Cambridge University Press, 2009.

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Aerospace propulsion systems. Singapore: Wiley, 2010.

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Conference papers on the topic "Scramjet (motor)"

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Pitthan Couto, Alan, Fortunato Martins Neto, Luiz Henrique Silva Marques Soares, João Felipe de Araújo Martos, and Paulo Gilberto de Paula Toro. "MODELAGEM DE UM MOTOR SCRAMJET AXISSIMÉTRICO." In 2º Congresso Aeroespacial Brasileiro. Santa Maria, Rio Grande do Sul: Even3, 2019. http://dx.doi.org/10.29327/2cab2019.224837.

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Renan Guilherme Santos Vilela, Thiago Victor Cordeiro Marcos, João Felipe de Araújo Martos, Jayme Rodrigues Teixeira da Silva, Ronaldo de Lima Cardoso, Antonio Carlos de Oliveira, Marco Antonio Sala Minucci, Israel da Silveira Rêgo, and Paulo Gilberto de Paula Toro. "Investigação Experimental de um motor scramjet de admissão interna." In IX Congresso Nacional de Engenharia Mecânica. Rio de Janeiro, Brazil: ABCM Associação Brasileira de Engenharia e Ciências Mecânicas, 2016. http://dx.doi.org/10.20906/cps/con-2016-0813.

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Amália Bondesan dos Santos, Maria, João Felipe de Araujo Martos, and Paulo Gilberto de Paula Toro. "PROJETO AEROTERMODINÂMICO DO SISTEMA DE ADMISSÃO DE UM MOTOR SCRAMJET." In 2º Congresso Aeroespacial Brasileiro. Santa Maria, Rio Grande do Sul: Even3, 2019. http://dx.doi.org/10.29327/2cab2019.224861.

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4

Rafael de Oliveira Santos, Marco Antônio Sala Minucci, Paulo Gilberto de Paula Toro, and Israel da Silveira Rêgo. "Concepção Aerotermodinâmica e Projeto Mecânico de um motor Scramjet de treinamento." In IX Congresso Nacional de Engenharia Mecânica. Rio de Janeiro, Brazil: ABCM Associação Brasileira de Engenharia e Ciências Mecânicas, 2016. http://dx.doi.org/10.20906/cps/con-2016-1175.

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5

Bao, Wen, Duo Zhang, Jiang Qin, and Weixing Zhou. "Performance Analysis on Fuel Turbo-pump and Motor System of Scramjet Engine." In 10th International Energy Conversion Engineering Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-4159.

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Toro, Paulo, João Lucas Correia Barbosa de Farias, George Marinho, Jonatha Araújo, Gilvan Borba, and Israel Rêgo. "UFRN’S INWARD ACADEMIC SCRAMJET COUPLED TO FTI ROCKET MOTOR TO DEMONSTRATE SUPERSONIC COMBUSTION." In Brazilian Congress of Thermal Sciences and Engineering. ABCM, 2018. http://dx.doi.org/10.26678/abcm.encit2018.cit18-0193.

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7

Mohamed, Ajmal K., Jerome Messineo, Jean-Yves Lestrade, Sebastien Defoort, Jacques Soutade, and Paul Viguier. "Tunable diode laser absorption spectroscopy of CO2 and H2O at 2.7 µm in a scramjet combustor and in exhaust gases of a hybrid rocket motor." In 32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-3548.

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