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.
| Identifer | oai:union.ndltd.org:IBICT/oai:agregador.ibict.br.BDTD_ITA:oai:ita.br:3190 |
| Date | 00 December 2016 |
| Creators | Iván Felipe Rodriguez Barón |
| Contributors | Paulo Gilberto de Paula Toro |
| Publisher | Instituto Tecnológico de Aeronáutica |
| Source Sets | IBICT Brazilian ETDs |
| Language | English |
| Detected Language | English |
| Type | info:eu-repo/semantics/publishedVersion, info:eu-repo/semantics/masterThesis |
| Format | application/pdf |
| Source | reponame:Biblioteca Digital de Teses e Dissertações do ITA, instname:Instituto Tecnológico de Aeronáutica, instacron:ITA |
| Rights | info:eu-repo/semantics/openAccess |
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