Propulsive jet influence on generic launcher base flow

Stephan, S.; Wu, Jie; Radespiel, Rolf

doi:10.1007/s12567-015-0098-9

Cited by 13 publications

(18 citation statements)

References 34 publications

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“…2. The model is installed in the wind tunnel with a sword-shaped strut support, fixed in a To investigate the influence of a propulsive jet on the launcher-wake flow in the HLB facility, the jet-simulation facility (TSA) described by Stephan et al [7] is integrated in the wind-tunnel model. This facility for the simulation of afterbody flows in the HLB facility works according to the same principle as the HLB itself, with a long heated storage tube that can be pressurized up to 140 bar and heated up to 900 K outside of the wind tunnel, and a tandem nozzle consisting of two nozzles and an intermediate settling chamber (see Fig.…”

Section: Wind Tunnel Jet-simulation Facility and Experimental Modelmentioning

confidence: 99%

“…3b). The measurement locations were chosen based on previous studies on the same model geometry [7,9]. A Spectrum M2i.4652 transient recorder was used to sample the pressure signals.…”

Section: Wind Tunnel Jet-simulation Facility and Experimental Modelmentioning

confidence: 99%

“…In the transonic range, Deprés et al [1], Deck and Thorigny [2], and Weiss et al [3] have investigated cases both with and without a propulsive jet. In supersonic flow, such cases have been studied by Bannink et al [4], Bourdon and Dutton [5], Janssen and Dutton [6], and Stephan et al [7,8], for example. Saile et al [9,10] and Statnikov et al [11] have studied hypersonic cases.…”

Section: Introductionmentioning

confidence: 99%

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Flow structure in the wake of a space-launcher model with propulsive-jet simulation

Schreyer

2020

CEAS Space J

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The flow around a space launcher is dominated by flow separation at the junction between the main body and engine and strongly influenced by the propulsive jet. The flow field is highly unsteady with strong local pressure and temperature loads. To conceive a means of mitigating these effects and allow for smarter launcher designs, a better understanding is necessary. The wake of a generic axisymmetric launcher model with and without afterexpanding propulsive jet was investigated at Mach 2.9, a Reynolds number Re D = 1.3 ⋅ 10 6 (model diameter D), and a nozzle exit velocity of the jet simulation of Mach 2.5. I observed the evolution of the flow and its spectral content with velocity measurements with particle image velocimetry and wall-pressure recordings. Coherent structures were analyzed based on a proper orthogonal decomposition. The propulsive jet has two major influences. First, the turbulent intensities in the shear layer are damped, and the larger structures in the wake contain less turbulent kinetic energy than in the baseline case without propulsive jet. Second, the reattachment process is modified and the wake instability phenomena change accordingly. Without propulsive jet, large-scale separation with reattachment on the nozzle fairing occurs and the low-frequency unsteadiness of the closed separation bubble/recompressionshock system is relevant. This phenomenon only has a minor influence under the influence of the jet plume, where the flow is displaced away from the surface and the reattachment process is incomplete. Here, shear-layer instabilities become more prominent.

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Section: Wind Tunnel Jet-simulation Facility and Experimental Modelmentioning

confidence: 99%

“…3b). The measurement locations were chosen based on previous studies on the same model geometry [7,9]. A Spectrum M2i.4652 transient recorder was used to sample the pressure signals.…”

Section: Wind Tunnel Jet-simulation Facility and Experimental Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Flow structure in the wake of a space-launcher model with propulsive-jet simulation

Schreyer

2020

CEAS Space J

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“…For details on this configuration of the HLB facility see Wu et al [11]. The experimental conditions for our present study were chosen to agree with the SFB TR40 supersonic test case (see for example Stephan et al [8]) and are summarized in Table 1.…”

Section: Wind Tunnel Jet Simulation Facility and Experimental Modelmentioning

confidence: 99%

“…In the transonic range, Deprés et al [1], Deck & Thorigny [3], and Weiss et al [4] have investigated cases both with and without propulsive jet. In supersonic flow, such cases were studied by Bannink et al [5], Bourdon & Dutton [6], Janssen & Dutton [7], and Stephan et al [8], for example. Saile et al [9,10] and Statnikov et al [2] studied hypersonic cases.…”

Section: Introductionmentioning

confidence: 99%

Flow structure and unsteadiness in the supersonic wake of a generic space launcher

Schreyer

Stephan

Radespiel

2016

54th AIAA Aerospace Sciences Meeting

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The wake flow of a generic axisymmetric space-launcher model with and without propulsive jet is investigated. Measurements are performed at Mach 2.9 and a Reynolds number Re D = 1.3 • 10 6 based on model diameter D, and the nozzle exit velocity of the jet is at Mach 2.5. Velocity measurements in the wake flow by means of Particle Image Velocimetry and mean and unsteady wall-pressure measurements on the main-body base are performed simultaneously. This way, the evolution of the wake flow was observed along with its spectral content. In this paper, the mean flow topology and turbulence behavior of the wake is described based on PIV measurements, and the influence of the afterexpanding jet plume is discussed. For the case without propulsive jet, a large separated zone is forming downstream of the main body shoulder and the flow is reattaching downstream on the nozzle fairing. Under the influence of the jet plume, the separated region is increased and reattachment does not occur anymore. The flow is displaced away from the wall. The jet plume appears to have a stabilizing effect on the wake flow. The development of the shear layer and the magnitude of the turbulent intensities are damped, which we showed with the axial and radial components of the turbulent velocity fluctuations, as well the Reynolds shear stress evolution along the launcher afterbody.

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Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher

Barklage

Radespiel

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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This work investigates the interaction of the afterbody flow with the propulsive jet flow on a generic space launcher equipped with two alternative nozzle concepts and different afterbody geometries. The flow phenomena are characterized by experimental measurements and numerical URANS and LES simulations. Investigations concern a configuration with a conventional truncated ideal contour nozzle and a configuration with an unconventional dual-bell nozzle. In order to attenuate the dynamic loads on the nozzle fairing, passive flow control devices at the base of the launcher main body are investigated on the configuration with TIC nozzle. The nozzle Reynolds number and the afterbody geometry are varied for the configuration with dual-bell nozzle. The results for integrated nozzles show a shift of the nozzle pressure ratio for transition from sea-level to altitude mode to significant lower levels. The afterbody geometry is varied including a reattaching and non-reattaching outer flow on the nozzle fairing. Investigations are performed at supersonic outer flow conditions with a Mach number of $$Ma_\infty =3$$. It turns out, that a reattachment of the outer flow on the nozzle fairing leads to an unstable nozzle operation.

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Propulsive jet influence on generic launcher base flow

Cited by 13 publications

References 34 publications

Flow structure in the wake of a space-launcher model with propulsive-jet simulation

Flow structure in the wake of a space-launcher model with propulsive-jet simulation

Flow structure and unsteadiness in the supersonic wake of a generic space launcher

Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher

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