{"id":{"repo_id":"aachen","oai_identifier":"oai:publications.rwth-aachen.de:61700"},"canonical_url":"https://search.dev.ndltd.org/etd/aachen/oai:publications.rwth-aachen.de:61700","repository":{"repo_id":"aachen","name":"RWTH Aachen University","base_url":"https://publications.rwth-aachen.de/oai2d"},"display":{"title":"Experimentelle Untersuchung der Innenverdichtung eines Hyperschalltriebwerkeinlaufs mit Überschalldurchströmung","abstract":"The main topic of the research project is the experimental investigation of the inner compression of ramjet inlets with supersonic combustion (scramjet). The work focuses on the isolator section, located between the Inlet and the combustion chamber. The main Task of the isolator is he deceleration of the incoming air to moderate supersonic mach numbers and thus an increase of pressure. Furthermore the isolator has to protect the inlet against the pressure fluctuations released by the combustion process. In the particular measurements the Isolator was charged with an asymmetric flow, as it will be given by an Scramjet-inlet. To achieve a database for the design of Isolator sections different geometries are tested at simulated flight mach numbers of M=3,3 and M=4. The investigations were done by use of conventional pressure and temperature measurements as well as a colour-schlieren-optic, allowing the visualisation of pressure gradients within the tested model. Special attentions were given to the stable operation of the shock and shock-train dominated flow. Using the optical system the shock systems and the shock boundary interaction could be visualised very well. A comparison between the experimental data and numerical calculations done in parallel leads to additional Information about the observed flow phenomena.","abstract_html":"The main topic of the research project is the experimental investigation of the inner compression of ramjet inlets with supersonic combustion (scramjet). The work focuses on the isolator section, located between the Inlet and the combustion chamber. The main Task of the isolator is he deceleration of the incoming air to moderate supersonic mach numbers and thus an increase of pressure. Furthermore the isolator has to protect the inlet against the pressure fluctuations released by the combustion process. In the particular measurements the Isolator was charged with an asymmetric flow, as it will be given by an Scramjet-inlet. To achieve a database for the design of Isolator sections different geometries are tested at simulated flight mach numbers of M=3,3 and M=4. The investigations were done by use of conventional pressure and temperature measurements as well as a colour-schlieren-optic, allowing the visualisation of pressure gradients within the tested model. Special attentions were given to the stable operation of the shock and shock-train dominated flow. Using the optical system the shock systems and the shock boundary interaction could be visualised very well. 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