12 research outputs found

    Joint European Effort Towards Advanced Rocket Thrust Chamber Technology

    Get PDF
    The achievements of the FSCD group during the last three years are described. For the case of nozzle flows in quiet ambience, new observations of the plume behaviour for truncated ideal nozzles are reported

    Experimental Investigation of Base Flow Buffeting on the ARIANE 5 Launcher Using High Speed PIV

    No full text
    Experiments have been performed on a 1:60 scale Ariane 5 launcher in the DNW HST wind tunnel by means of two-component particle image velocimetry (2C-PIV). Measurements are performed for Mach 0.5 and Mach 0.8. The investigation focuses on studying the flow-buffeting phenomenon in the base of an Ariane V rocket. In total four configurations are tested: reference configuration, skirt, scoop and reference configuration without struts. It has been found that the presence of the struts has a large effect on the flow field; the secondary flow caused by the struts decreases the separated region and increases the overall turbulence. The skirt has the effect that the shear layer separates later and therefore does not reattach on the nozzle. Also in the separated region a secondary recirculation region is formed. For the scoop configuration it was observed that a second wake was formed by the scoop element causing the overall shear layer to become thicker. Finally using POD analysis two dominant modes are identified that can be associated to the separation bubble and shear layer dynamics

    Plug nozzles : assessment of prediction methods for flow features and engine performance

    No full text
    Communication to : 40th AIAA aerospaces sciences meeting and exhibit, Reno (USA), January 14-17, 2002SIGLEAvailable from INIST (FR), Document Supply Service, under shelf-number : 22419, issue : a.2002 n.181 / INIST-CNRS - Institut de l'Information Scientifique et TechniqueFRFranc

    Launch Vehicle Base Buffeting - Recent Experimental and Numerical Investigations

    No full text
    During atmospheric ascent of launcher configurations, a massively separated flow environment in the base region of the launcher can generate strong low frequency wall pressure fluctuations. The nozzle structure can be subjected to dynamic loads resulting from these pressure fluctuations. The loads are usually most severe during the high dynamic pressure phase of flight at transonic speeds and the aerodynamic excitation can induce a response of the structural modes called buffeting. In order to obtain a deeper insight into base buffeting related to the Ariane 5 launch vehicle, a set of experiments was performed in the DNW HST wind tunnel in close cooperation with the utilization of modern CFD tools (hybrid RANS/LES). During the test campaign a 1/60 scale Ariane 5 launcher test article was utilized, and detailed unsteady pressure measurements in the base region of the model were for the first time performed in conjunction with time resolved velocity field measurements using PIV. The work was performed in the framework of the ESA TRP “Unsteady Subscale Force Measurements within a Launch Vehicle Base Buffeting Environment”
    corecore