A. Barklage, R. Radespiel

The wake flow jet interaction of a generic space launcher with an integrated dual-bell nozzle as main propulsion unit is investigated with special regard to the boundary layer state inside the nozzle. Results were obtained by experimental measurements in a supersonic wind tunnel facility and by numerical RANS simulations. A dual-bell nozzle is an altitude compensating nozzle that promises a significant payload gain compared to conventional nozzles. Though the dual-bell nozzle was investigated in several previous studies, the interaction with an outer flow was not analysed yet. First studies with a supersonic outer flow showed an unsteady separation known as flip-flop effect in the nozzle for a wide range of nozzle total pressures. The origin of this phenomenon is not known; it could be caused by a laminar boundary layer in the nozzle. Therefore, experimental measurements with boundary layer tripping in the form zig-zag tape applied in the nozzle are conducted. Numerical RANS simulations with transition prescription are used to verify an appropriate position for the zig-zag tape. It turns out, that the zig-zag tape has a significant influence on the transition between the different operating modes of the nozzle, which is shifted to lower chamber pressures. However, the appearance of the flip-flop effect was not avoided by the use of boundary layer tripping.

Deutscher Luft- und Raumfahrtkongress 2018, Friedrichshafen

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2019

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

urn:nbn:de:101:1-2019012513511995349812

Experimentelle Aerodynamik, Supersonische Strömungen

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Barklage, A.; Radespiel, R. (2019): Influence of the Boundary Layer State on the Transition of a Dual-Bell Nozzle. Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.. (Text). urn:nbn:de:101:1-2019012513511995349812.

25.01.2019