Einfluss des Treibergases auf die Strömung in Stoßwellenkanälen

One of the main aspects of space transportation is the aerodynamic of space vehicles. For the investigation of flow problematic and the interrelated transport phenomenas in hypersonic flows, the development of suitable tools is required. Here, development and verification of such tools is represented. On the experimental side a probe for the measurement of the static pressure inside hypersonic wind tunnels is described, on the numerical side the modification of a two dimensional axissymmetric navier stokes solver for the simulation of multispecies flow. The influence of the driver gas to the flow inside shock tunnels is investigated. Through it one basic problem of shock tunnels is detected. Due to the working principal, test and driver gases will be mixed up. Hence the contamination of the test gas yields to inadvertent flow phenomenas. With the here described analysis the mixing of both gases during test runs of shock tunnels can be proved.

Grantor dc:publisher

Publikationsserver der RWTH Aachen University

Year dc:date

2000

Author dc:creator

• Kindl, Helmut

Contributors dc:contributor

• Olivier, Herbert

• info:eu-repo/classification/ddc/530
• Hyperschallströmung
• Stoßwellenrohr
• Anströmung
• Druckmessung
• Navier-Stokes-Gleichung
• Numerisches Verfahren
• Physik
• Verdichtetes Gas
• Stoßwelle
• Windkanalströmung

Statement dc:rights

• info:eu-repo/semantics/openAccess

Language dc:language

ger

Identifier

https://publications.rwth-aachen.de/search?p=id:%22RWTH-CONV-208129%22

OAI record oai:identifier

https://publications.rwth-aachen.de/oai2d?verb=GetRecord&metadataPrefix=oai_dc&identifier=oai%3Apublications.rwth-aachen.de%3A56528