Experimental investigation of the scramjet demonstrator 14-X B with mach number of 6 to 12 in the hypersonic shock tunnel

• Ano de defesa: 2016
• Autor(a) principal: Iván Felipe Rodriguez Barón
• Tipo de documento: Dissertação
• Tipo de acesso: Acesso aberto
• Idioma: eng
• Instituição de defesa: Instituto Tecnológico de Aeronáutica
• Palavras-chave em Português: Aeronaves hipersônicas; Fuselagens; Aerotermodinâmica; Foguetes; Propulsão supersônica; Hipersônica; Engenharia aeroespacial; Engenharia aeronáutica
• Link de acesso: http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=3190

This work presents an experimental investigation carried out in the Hypersonic Shock Tunnel T3, using the 1:2 scale model of the scramjet technology demonstrator 14-X B, developed at the Laboratory of Aerothermodynamic and Hypersonic Prof. Henry T. Nagamatsu belonging to the Instituto de EstudosAvançados (IEAv). The scramjet demonstrator 14-X B was installed parallel to the free-stream hypersonic flow at angle of attack 0 and Mach numbers 6 to 12 approximately. On the scramjet demonstrator 14-X B lower surface, flush mount piezoelectric pressure transducers are installed to measure the pressure distribution along the model central streamline (longitudinal symmetry line) and off-line. A piezoelectric pressure transducer is installed at the leading edge of the model 14-X B (pitot tube) to measure the freestream total pressure and to infer the airflow speed of the hypersonic flow in the test section of the hypersonic shock tunnel T3. In addition, a theoretical analysis based on the viscous hypersonic flow is applied to airflow over the airframe scramjet engine. The experimental results are collected and analyzed, showing a reasonable agreement with the theoretical ones.