| Autor: |
Iván Felipe Rodriguez Barón |
| Jazyk: |
angličtina |
| Rok vydání: |
2016 |
| Předmět: |
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| Zdroj: |
Biblioteca Digital de Teses e Dissertações do ITAInstituto Tecnológico de AeronáuticaITA. |
| Druh dokumentu: |
masterThesis |
| Popis: |
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. |
| Databáze: |
Networked Digital Library of Theses & Dissertations |
| Externí odkaz: |
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