S. Stephan, R. Radespiel, R. Müller-Eigner

Afterbody flow phenomena represent a major source of uncertainties in the design of a launcher. Therefore there is a demand for measuring such flows in a wind tunnel. As a new approach to propulsive jet simulation a new jet facility was integrated into a hypersonic wind tunnel. This jet simulation facility resembles a Vulcain 2 rocket motor integrated into an Ariane 5 launcher. Details about the design and first experimental results are reported. This includes measurements of pressure, temperature and Mach number distribution.

Deutscher Luft- und Raumfahrtkongress 2012, Berlin

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2012

Conference Paper

englisch

21,0 x 29,7 cm, 8 Seiten

urn:nbn:de:101:1-201211021667

launchers, hypersonic wind tunnels, Ludwiegrohr, rocket engines, Treibstrahlsimulation

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02.11.2012