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Title: A new approach to optimize the scramjet inlet design applying the total pressure recovery
Authors: Fernandes, Alef Giovane Lima do Nascimento
Keywords: Scramjet. Supersonic combustion ramjet. Hypersonic airbreathing propulsion.
Issue Date: 5-Dec-2019
Publisher: Universidade Federal do Rio Grande do Norte
Citation: FERNANDES, Alef Giovane Lima do Nascimento. A new approach to optimize the scramjet inlet design applying the total pressure recovery. 2019. 9 f. Trabalho de Conclusão de Curso (Graduação em Engenharia Mecânica) - Centro de Tecnologia, Departamento de Engenharia Mecânica, Universidade Federal do Rio Grande do Norte, Natal, 2019.
Portuguese Abstract: A generic hypersonic airbreathing propulsion based on supersonic combustion ramjet (scramjet) technology has been designed, at the Universidade Federal do Rio Grande do Norte (UFRN), using analytical theoretical analysis (engineering approach). A two-dimensional hydrogen powered generic scramjet inlet has been designed to demonstrate, in atmospheric flight, a supersonic combustion, of atmospheric air (in supersonic speed) with hydrogen, on an acceleration mission to 2050 m/s (Mach number 6.8) at 30 km geometric altitude. In general in a preliminary design, one-dimensional compressible flow (shock wave) theory, which may readily describe many features of compression region of the airbreathing engine, may used to estimate the shock wave angles, thermodynamic properties and the velocities (Mach numbers) of the hypersonic atmospheric air flow, at the generic scramjet inlet. However, the deflection angles of the compression ramps are known. Design and optimization of a 2-D mixed compression generic scramjet models are investigated by the extended Oswatitsch classical optimization of a 2-D supersonic inlet procedure to scramjet inlets. The deflection angles of compression section ramps and the corresponding thermodynamic property ratio (pressure, temperature and specific mass) of the airflow as well as the airflow velocities (and corresponding Mach numbers) are obtained by the present optimization criterion. The present optimization criterion is defined based on the system of (n-1) incident oblique shockwaves, with the equal strength, and one reflected oblique shockwave establish in the external and internal compression section, respectively, which reduce the known hypersonic flow (pressure, temperature, specific mass and flow velocity) to a supersonic flow, with required temperature and velocity, at the entrance of a combustion chamber. Therefore, the maximum shock pressure recovery is obtained as function of the incident oblique shockwaves of equal strength. Thermodynamic property ratio (pressure, temperature and specific mass) as well as the flow velocities (and corresponding Mach numbers) are presented for seven incident oblique shockwaves.
Other Identifiers: 20180154459
Appears in Collections:Engenharia Mecânica

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