Computation of turbulent supersonic flows around pointed bodies having crossflow separation

Degani, David; Schiff, Lewis B.

doi:10.1016/0021-9991(86)90059-8

Cited by 260 publications

(48 citation statements)

References 6 publications

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“…These models rely on the boundary layer concept, usually incorporating separate formulas for the inner and outer layers, and they require an estimate of a length scale which depends on the thickness of the boundary layer. The estimation of this quantity by a search for a maximum of the vorticity times a distance to the wall, as in the Baldwin-Lomax model, can lead to ambiguities in internal flows, and also in complex vortical flows over slender bodies and highly swept or delta wings [47,125]. The Johnson-King model [98], which allows for non-equilibrium effects through the introduction of an ordinary differential equation for the maximum shear stress, has improved the prediction of flows with shock induced separation [168,101].…”

Section: Turbulence Modelingmentioning

confidence: 99%

A perspective on computational algorithms for aerodynamic analysis and design

Jameson

2001

Progress in Aerospace Sciences

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This paper examines the use of computational fluid dynamics as a tool for aircraft design. It addresses the requirements for effective industrial use, and trade-offs between modeling accuracy and computational costs. Essential elements of algorithm design are discussed in detail, together with a unified approach to the design of shock capturing schemes. Finally, the paper discusses the use of techniques drawn from control theory to determine optimal aerodynamic shapes. In the future multidisciplinary analysis and optimization should be combined to take account of the trade-offs in the overall performance of the complete system.

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Section: Turbulence Modelingmentioning

confidence: 99%

A perspective on computational algorithms for aerodynamic analysis and design

Jameson

2001

Progress in Aerospace Sciences

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“…High-order space accuracy is obtained using the MUSCL, using the primitive variable interpolation. The viscous terms are evaluated by central differencing and the eddy viscosity is modeled by the Baldwin-Lomax turbulence model 13) with Degani-Schiff correction 14) implemented. Only the steady-state solutions are considered, and the LU-ADI factorization time integration algorithm 15) is used.…”

Section: Methodsmentioning

confidence: 99%

Flow Field and Performance Analysis of Aerospike Nozzles with Simplified Clustered Modules

Ito

Fujii

2004

Trans. Japan Soc. Aero. S Sci.

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The fundamental characteristics of simplified clustered aerospike nozzles are analyzed by the computational fluid dynamics approach. Several types of aerospike nozzles, having 6, 12 and 24 inner nozzle modules with the same area ratio and total flow rate, are examined. The interactions of the exhaust flows from the neighboring modules create shock waves, which produce high-pressure regions on the nozzle surface. The base regions of the cluster-type aerospike nozzles are not influenced by the clustering of the modules and show features similar to axisymmetric-type aerospike nozzles. The base pressure is nearly equal to the environmental pressure when the pressure ratio is low and suddenly attains a constant pressure when the pressure ratio is high. The computed results show that the number of modules influence the thrust performance, and the major reason for the decrease in thrust performance with a smaller number of modules is due to thrust loss in the ramp region.

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“…If a global maximum value is used, the computed turbulence viscosity might be wrong, because the one needed in this model is the first maximum value of F(n) near the wall. This problem was first analyzed by Degani and Schiff [7]. They found that the behavior of F(n) is different for the attached flow region and the separated flow region.…”

Section: Drawbacks and Modifications Of The B-l Modelmentioning

confidence: 97%

“…Goldberg and Chakravarthy [10] proposed an algebraic k -turbulence model in which the inner layer viscosity is evaluated by a new formula instead of the Baldwin-Lomax one. In this study, both Degani and Schiff's [7] and Marx's [8] modifications have been employed.…”

Section: Drawbacks and Modifications Of The B-l Modelmentioning

confidence: 99%