Large Eddy Simulations of Supersonic Turbulent Reacting Flows

Banaeizadeh, Araz; Li, Zhaorui; Jaberi, Farhad

doi:10.2514/6.2010-202

Cited by 4 publications

(4 citation statements)

References 18 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The authors indicated that they will revisit the coaxial jet case with the more sophisticated closures as their development is completed. A number of additional cases have been simulated with LES/FDF methods including high-speed mixing 152 , flows with shocks 153 and combusting flows. [154][155][156][157] One of these interesting cases considered the LES of turbulent nonreacting and reacting flow in an axisymmetric dump combustor.…”

Section: Les/fdf Methods For High-speed Reacting Flowsmentioning

confidence: 99%

Development of Methods to Predict High-Speed Reacting Flows in Aerospace Propulsion Systems

Drummond

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

This paper discusses the current state-of-the-art of computational capabilities for predicting reacting flows in high-speed aerospace propulsion systems with an emphasis on the flow fields in scramjets. We begin with a review of the history of efforts to model the scramjet environment and then concentrate on more recent activities that lead to today's capabilities. The NASP technology program provided strong motivation for advancing the computational capabilities of the country in both the government and private sectors. Required ground test facilities with sufficient test times were limited to around Mach 8, and higher Mach numbers, achievable in pulse facilities, could only be maintained for the order of milliseconds. In addition, the number of facility cycles available to parameterize a given engine flow path were limited, and the facilities were expensive to operate. Computational capabilities were needed to fill both of these gaps. While the NASP program was not successful in developing a vehicle, it did spawn the development of new computational algorithms. The Hyper-X Program beginning in 1995 revived high-speed computational research and development. A flight program is the catalyst that drives technology development and synthesizes all of the efforts into a unified tool for development of the ultimate experiment, the flight of a hypersonic vehicle. The genesis of most of the current day state-of-the-art computational tools for scramjet research and development began with this program. This paper attempts to cover this story from NASP and Hyper-X to the present day.

show abstract

Section: Les/fdf Methods For High-speed Reacting Flowsmentioning

confidence: 99%

Development of Methods to Predict High-Speed Reacting Flows in Aerospace Propulsion Systems

Drummond

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

show abstract

“…The approximation used in this paper is based on the work of Hsu et al [45,17]. It later has been employed in the same way by Möbus et al [18,20] for compressible RANS and similarly by Banaeizadeh et al [46,22] for compressible LES/FMDF simulations. By inserting these modeling approaches in Eq.…”

Section: Partially Modeled Mdf Transport Equationmentioning

confidence: 99%

Lagrangian transported MDF methods for compressible high speed flows

Gerlinger

2017

Journal of Computational Physics

View full text Add to dashboard Cite

This paper deals with the application of thermochemical Lagrangian MDF (mass density function) methods for compressible sub-and supersonic RANS (Reynolds Averaged Navier-Stokes) simulations. A new approach to treat molecular transport is presented. This technique on the one hand ensures numerical stability of the particle solver in laminar regions of the flow field (e.g. in the viscous sublayer) and on the other hand takes differential diffusion into account.It is shown in a detailed analysis, that the new method correctly predicts first and second-order moments on the basis of conventional modeling approaches.Moreover, a number of challenges for MDF particle methods in high speed flows is discussed, e.g. high cell aspect ratio grids close to solid walls, wall heat transfer, shock resolution, and problems from statistical noise which may cause artificial shock systems in supersonic flows. A Mach 2 supersonic mixing channel with multiple shock reflection and a model rocket combustor simulation demonstrate the eligibility of this technique to practical applications. Both test cases are simulated successfully for the first time with a hybrid finite-volume (FV)/Lagrangian particle solver (PS).

show abstract

“…A number of additional cases have been simulated with LES/FDF methods including high-speed mixing [167], flows with shocks [168], and combusting flows [169][170][171][172]. One of these interesting cases considered the LES of turbulent nonreacting and reacting flow in an axisymmetric dump combustor [172].…”

Section: Les/filtered Density Function Methods For High-speed Reacmentioning

confidence: 99%

Methods for Prediction of High-Speed Reacting Flows in Aerospace Propulsion

Drummond

2014

AIAA Journal

View full text Add to dashboard Cite

Large Eddy Simulations of Supersonic Turbulent Reacting Flows

Cited by 4 publications

References 18 publications

Development of Methods to Predict High-Speed Reacting Flows in Aerospace Propulsion Systems

Development of Methods to Predict High-Speed Reacting Flows in Aerospace Propulsion Systems

Lagrangian transported MDF methods for compressible high speed flows

Methods for Prediction of High-Speed Reacting Flows in Aerospace Propulsion

Contact Info

Product

Resources

About