Numerical Prediction and Experimental Validation of Unsteady Loads on ARIANE5 and VEGA

Schwane, Richard

doi:10.2514/1.a32793

Cited by 17 publications

(11 citation statements)

References 5 publications

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“…The flow regime of interest is transonic, since this is where the launcher is exposed to strong unsteady loads. Schwane (2015) reports pressure fluctuations with increasing amplitude for the first 37 s of the Ariane 5 Flight A501. David and Radulovic (2005) present pressure measurements taken during flight, which show that the strongest and most distinct frequency of Ariane 5 loads on the main engine occur for Mach 0.8.…”

Section: Introductionmentioning

confidence: 99%

On the subsonic near-wake of a space launcher configuration without jet

2019

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Wake flows have been extensively investigated in the past mainly with the objective to reduce drag. The failure of Ariane 5 Flight 157 though revealed that the understanding has not been sufficient, which triggered a new series of base-flow investigations. Most of them scrutinized the dynamics of the flow at one specific point along the flight path either in the subsonic, transonic, or supersonic range. However, no coherent image of the flow topology development in terms of a parametric study is available so far. The current work addresses the question of a near-wake scaling of a generic space launcher configuration. This question is tackled experimentally by means of particle image velocimetry measurements in the vertical test section Cologne in the range of Mach 0.5, 0.6, 0.7, 0.8, and 0.9 for Reynolds numbers between Re D = 0.8 × 10 6 and 1.7 × 10 6. Results show the mean, the turbulence intensity, and the Reynolds shear stress distribution in the wake in comparison with the literature. In addition, data to the incoming boundary layer are provided and to the evolving shear layer. In that regime, the results indicate that the velocity and Reynolds stresses might be independent from the Mach and Reynolds number if scaled with the reattachment length. If this hypothesis holds true, it might be useful for the validation of numerical codes and for the initial determination of the flow field of space launchers in the design phase.

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Section: Introductionmentioning

confidence: 99%

On the subsonic near-wake of a space launcher configuration without jet

2019

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“…It turns out that axisymmetric body experiments are usually not representative for a configuration with boosters. Schwane [44] discusses efficient methods for spacecraft design and optimization using numerical and experimental flow and structure data from Ariane 5 and Vega experiments. Schwane showed that these complex unsteady flow topologies have to be monitored carefully relating to data post-processing, filtering and statistical convergence.…”

mentioning

confidence: 99%

Propulsive jet influence on generic launcher base flow

Stephan

Radespiel

2015

CEAS Space J

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“…In resonance, the interaction between aerodynamic and structural loads can have disastrous consequences. The studies of David and Radulovic (2005), Schwane (2015) have found that flow conditions are especially detrimental for Ariane 5 in the transonic flow regime, in particular, at Mach 0.8.…”

Section: Introductionmentioning

confidence: 98%

“…The failed flight has triggered many studies to improve and extend the understanding of base flow phenomena. Investigations on similar base geometry representations for Ariane 5 have been conducted by Wong et al (2007), Schrijer et al (2011, Schwane (2015). On generic configurations, the governing mechanisms for buffeting have been analyzed among others by Fuchs et al (1979), Deprés et al (2004), Deck and Thorigny (2007), Weiss et al (2009), Weiss and Deck (2013), Schrijer et al (2014), Scharnowski (2013), Scharnowski et al (2015), Scharnowski et al (2016), Statnikov et al (2016), Statnikov et al (2017), van Gent et al (2017b), andvan Gent et al (2017a).…”

Section: Introductionmentioning

confidence: 99%

On subsonic near-wake flows of a space launcher configuration with various base geometries

2021

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Buffet/buffeting as load imposing mechanism on the base structures of space launcher has been of strong interest ever since it was found as partially responsible for the failed flight 157 of Ariane 5. Several studies suggested that the base region is most excited at Mach 0.8. A preceding study of the current series on base flow effects revealed a differing excitation in comparison to the other subsonic Mach number cases. It featured an especially pronounced excitation in the recirculation region. Thus, the current work attempts to answer the question why this case appears to be distinct. This is done by decreasing the relative nozzle length and focusing on the Reynolds stress distribution. The research question is approached by experiments in the ‘Vertical Test Section Cologne’ (VMK) on a base model with supersonic, over-expanded exhaust jet exposed to an ambient flow at Mach 0.8 and a Reynolds number of $$1.4\cdot 10^6$$ 1.4 · 10 6 . Data are acquired by means of particle image velocimetry (PIV) and high-speed schlieren imaging. The results reveal that a most unfavorable configuration appears to exist, which is if the mean shear layer reattachment takes place just on the tip of the nozzle. Graphic abstract

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Numerical Prediction and Experimental Validation of Unsteady Loads on ARIANE5 and VEGA

Cited by 17 publications

References 5 publications

On the subsonic near-wake of a space launcher configuration without jet

On the subsonic near-wake of a space launcher configuration without jet

Propulsive jet influence on generic launcher base flow

On subsonic near-wake flows of a space launcher configuration with various base geometries

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