A Nozzle Concept to Entrain Atmospheric Air for Ejector Operation

Cerantola, D. J.; Etele, Jason

doi:10.2514/6.2006-8089

Cited by 10 publications

(6 citation statements)

References 5 publications

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“…The use of multiple rockets arranged in an annular pattern requires considerable duplication of equipment and a reduction in available entrainment area. Therefore, this paper presents a means of creating an annular rocket exhaust stream while maintaining a single, circular throat section (Cerantola and Etele [29]). The resulting nozzle is housed within a three-component geometry that is designed to minimize flow separation (Waung and Etele [30]).…”

mentioning

confidence: 99%

Exchange Inlet Design for Rocket-Based Combined-Cycle Engines

Etele

Waung

Cerantola

2012

Journal of Propulsion and Power

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A methodology is presented for generating an inlet containing an entrained flow surrounded by an annular flow of driving, supersonic gas. As the driving flow expands outward into an annular pattern, it maintains a circular throat area while allowing the entrained flow to be drawn toward the axisymmetric axis. The methodology accounts for both compressibility and viscous effects, and it can be scaled for a variety of operating conditions and driving gases. Designs are presented for the inlet to an example rocket-based combined-cycle engine based on both a kerosenefueled and a hydrogen-fueled rocket. Numerical results are presented, showing rocket exhaust patterns that contain uniform conditions over 75% of the annular exhaust area. The entrained air passage is also shown to have high total pressure recovery over the subsonic flight range. The predicted performance is shown to be within 10% of the numerical simulations over the range of conditions considered.

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confidence: 99%

Exchange Inlet Design for Rocket-Based Combined-Cycle Engines

Etele

Waung

Cerantola

2012

Journal of Propulsion and Power

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“…A novel type of RBCC rocket nozzle geometry, shown in figure 1.5, has been proposed by Cerantola and Etele [16,17] with the goal of reducing ejector mixing lengths by increasing the shear layer area of the rocket exhaust stream while retaining a circular throat area. Maintaining a circular throat area allows this rocket nozzle geometry to be adapted to existing rocket engines.…”

Section: Novel Rbcc Rocket Nozzlementioning

confidence: 99%

An ejector air intake design method for a novel rocket-based combined-cycle rocket nozzle

Waung¹

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The author has granted a nonexclusive license allowing Library and Archives Canada to reproduce, publish, archive, preserve, conserve, communicate to the public by telecommunication or on the Internet, loan, distribute and sell theses worldwide, for commercial or noncommercial purposes, in microform, paper, electronic and/or any other formats.L'auteur a accorde une licence non exclusive permettant a la Bibliotheque et Archives Canada de reproduce, publier, archiver, sauvegarder, conserver, transmettre au public par telecommunication ou par I'lnternet, preter, distribuer et vendre des theses partout dans le monde, a des fins commerciales ou autres, sur support microforme, papier, electronique et/ou autres formats.Bien que ces formulaires aient inclus dans la pagination, il n'y aura aucun contenu manquant.

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“…The rocket flowpath developed by Cerantola and Etele [55,60] was designed to match the performance of the Atlas E/F LR-105-5 sustainer engine. The specifications used to approximate the kerosene C^i^/air LR-105-5 engine are given in Table 4.1.…”

Section: Atlas E/f Lr-105-5mentioning

confidence: 99%

Exchange inlet design optimization by genetic algorithm

Chorkawy¹

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A Nozzle Concept to Entrain Atmospheric Air for Ejector Operation

Cited by 10 publications

References 5 publications

Exchange Inlet Design for Rocket-Based Combined-Cycle Engines

Exchange Inlet Design for Rocket-Based Combined-Cycle Engines

An ejector air intake design method for a novel rocket-based combined-cycle rocket nozzle

Exchange inlet design optimization by genetic algorithm

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