Experimental and Analytical Design Verification of the Dual-Bell Concept

Hagemann, G.; Terhardt, M.; Haeseler, D.; Frey, Manuel

doi:10.2514/2.5905

Cited by 45 publications

(14 citation statements)

References 4 publications

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“…Since the exact nozzle geometry was not given in Ref. [30], an alternative way of validation has been sought. To put on evidence the correctness of the results, the computed shape has been fixed and some off-design conditions of the nozzle are investigated by a direct, laminar solver.…”

Section: Dual Bell Nozzlementioning

confidence: 99%

“…The pressure distribution imposed on the upper boundary is a spline fitting of the experimental data given in Ref. [30] (with symbol -x-in Fig. 21) and refers to the case of adapted nozzle.…”

Section: Dual Bell Nozzlementioning

confidence: 99%

“…Because of the higher area ratio, an increase in vacuum performance is achieved. The overall design parameters are kept from Hagemann et al [30] and refer to the truncated ideal base nozzle and a nozzle extension with favourable wall pressure gradient (TICNP). The numerical tests was solved on a 100 · 52 stretched grid.…”

Section: Dual Bell Nozzlementioning

confidence: 99%

See 2 more Smart Citations

A viscous inverse method for aerodynamic design

Ferlauto¹,

Marsilio²

2006

Computers & Fluids

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Section: Dual Bell Nozzlementioning

confidence: 99%

Section: Dual Bell Nozzlementioning

confidence: 99%

See 1 more Smart Citation

A viscous inverse method for aerodynamic design

Ferlauto¹,

Marsilio²

2006

Computers & Fluids

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“…One possible solution is to adapt the nozzle contour during flight to changes of ambient pressure mechanically, however the weight and mechanical complexities of such device is a big issue [1]. One of the most promising non-mechanical altitude compensating nozzles is the DBN [8,9,10]. It is a combination of two bell nozzles with different exit area ratios.…”

Section: Introductionmentioning

confidence: 99%

“…While the high side load peak occurs during transition because the flow is potentially separates asymmetrically within the nozzle extension [13]. Many studies have been done on the DBN to understand the transition and side loads generation numerically [14,15,16,17,18] and experimentally [9,19,20,21]. From the literature survey about the nozzle flow separation and side loads, it can be concluded that the key to decrease the side loads is to control the flow separation at all operating conditions.…”

Section: Introductionmentioning

confidence: 99%

Numerical Assessment of the Backward Facing Steps Nozzle

.¹

2015

IJRET

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The backward facing steps nozzle (BFSN) is a flow adjustable exit area nozzle for large rocket engines. It consists of two parts, the first is a base nozzle with small area ratio and the second part is a nozzle extension with surface consists of backward facing steps. The number of steps and their heights are carefully chosen to produce controlled flow separation at steps edges that adjust the nozzle exit area at all altitudes (pressure ratios). The BFSN performance parameters are assessed in terms of thrust and side loads against the dual-bell nozzle (DBN) with the same pressure ratios and cross sectional areas. The DBN is a two-mode flow adjustable exit area nozzle for low and high altitude. Three-dimensional turbulent flow solutions are obtained for the BFSN indicating that the flow is axi-symmetric and does not generate significant side loads. Further confirmation of the axi-symmetric flow is obtained by comparing the three-dimensional flow with the two-dimensional axi-symmetric solutions. The comparison of the thrust generated over the PR range from 50 to 1500 shows that BFSN generates more uniform and higher thrust than the DBN in the intermediate pressure ratios. At PR 1500 (high altitude), the BFSN thrust is 0.28% less than the DBN. All numerical solutions are obtained using the Fluent code.

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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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Experimental and Analytical Design Verification of the Dual-Bell Concept

Cited by 45 publications

References 4 publications

A viscous inverse method for aerodynamic design

A viscous inverse method for aerodynamic design

Numerical Assessment of the Backward Facing Steps Nozzle

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

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