Two Different Theoretical Approaches to the Base Pressure Problem in Two-Dimensional Supersonic Flow

Tanner, M.

doi:10.1017/s0001925900008374

Cited by 4 publications

(2 citation statements)

References 7 publications

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“…This method has been shown to provide good agreement with experimental results for a wide range of conditions (19)(20)24) .…”

Section: The Methods Of Tannermentioning

confidence: 67%

“…This process, however, takes no account of the base pressure produced by the flow-field. It has therefore been extended to allow estimation of this contribution to thrust by incorporating a technique developed for analysis of blunt-based projectiles by Tanner (19,20) . This requires some adaption to allow its application to the problem of pintle base pressure prediction on ED nozzles, and hence a brief outline of the method, focusing on these alterations, is presented.…”

Section: General Behaviourmentioning

confidence: 99%

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Optimising expansion deflection nozzles for vacuum thrust

Taylor

Hempsell

2004

Aeronaut. j.

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While expansion deflection (ED) nozzles have traditionally been considered primarily for use as altitude compensating devices to improve the performance of single stage to orbit vehicles, they also offer the potential for enhancing high altitude propulsion systems. If intended to only operate in near vacuum conditions, the complexity of analysis and inherent risks involved in the ED concept are greatly reduced. An integrated approach to the design and performance analysis of such nozzles is presented, comprising a mixture of computational fluid dynamics, the method of characteristics, and a semi-empirical model to allow full analysis of the closed wake flow-field of an ED nozzle. While it is demonstrated that the influence of the parameters used to define the throat region is critical to the successful application of the ED nozzle, it is also shown that with careful design the weight savings possible are significant. The analysis method itself is flexible and rapid, and lends itself well to incremental improvements in accuracy as the flow under consideration becomes better understood.

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“…This method has been shown to provide good agreement with experimental results for a wide range of conditions (19)(20)24) .…”

Section: The Methods Of Tannermentioning

confidence: 67%

Section: General Behaviourmentioning

confidence: 99%

Optimising expansion deflection nozzles for vacuum thrust

Taylor

Hempsell

2004

Aeronaut. j.

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Entropy method for calculating separated-flow parameters

Kalugin¹

1997

Fluid Dyn

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Simulation of Trailing Edge Vortex Shedding in a Transonic Turbine Cascade

Currie

Carscallen

1998

Journal of Turbomachinery

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Midspan losses in the NRC transonic turbine cascade peak at an exit Mach number (M2) of ~1.0 and then decrease by ~40 percent as M2 is increased to the design value of 1.16. Since recent experimental results suggest that the decrease may be related to a reduction in the intensity of trailing edge vortex shedding, both steady and unsteady quasi-three-dimensional Navier–Stokes simulations have been performed with a highly refined (unstructured) grid to determine the role of shedding. Predicted shedding frequencies are in good agreement with experiment, indicating the blade boundary layers and trailing edge separated free shear layers have been modeled satisfactorily, but the agreement for base pressures is relatively poor, probably due largely to false entropy created downstream of the trailing edge by numerical dissipation. The results nonetheless emphasize the importance of accounting for the effect of vortex shedding on base pressure and loss.

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Two Different Theoretical Approaches to the Base Pressure Problem in Two-Dimensional Supersonic Flow

Cited by 4 publications

References 7 publications

Optimising expansion deflection nozzles for vacuum thrust

Optimising expansion deflection nozzles for vacuum thrust

Entropy method for calculating separated-flow parameters

Simulation of Trailing Edge Vortex Shedding in a Transonic Turbine Cascade

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