Computational study of flow in a rocket-based combined cycle (RBCC) engine inlet

Reddy, D. R.; Sree, Dave

doi:10.1016/j.compfluid.2006.01.010

Cited by 7 publications

(4 citation statements)

References 20 publications

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“…This leads to a design in which the duct mass can become prohibitive. Therefore, alternative RBCC engine geometries have been proposed including axisymmetric geometries with several small distributed rockets (Escher [7]) or the semi-axisymmetric geometry proposed for the NASA GTX concept vehicle [8][9][10]. Considerable work has also been done on the strutjet engine, which has a rectilinear geometry and uses rockets mounted within the base of several struts [11][12][13][14][15][16][17].…”

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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 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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“…The air intake walls are specified as no-slip adiabatic walls which is consistent with the wall boundaries used by Reddy and Sree [52] in their RBCC inlet simulations, which used the NPARC Navier-Stokes code. The domain walls downstream of plane 3 are defined shown in figure 5.2.…”

Section: Flow Domain and Boundary Conditionsmentioning

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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“…Furthermore, it is known that the k-epsilon model is computationally quicker than the SST model, but it is also known that for regions of reverse flow the k-epsilon model over predicts separation [31]. In addition, the SST model is also used as the turbulence model for many other RBCC studies [17,32,33].…”

Section: Fluid Modelmentioning

confidence: 99%

Simulation of a rocket base combined cycle exchange inlet at subsonic conditions

Yuen¹

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Computational study of flow in a rocket-based combined cycle (RBCC) engine inlet

Cited by 7 publications

References 20 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

Simulation of a rocket base combined cycle exchange inlet at subsonic conditions

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