Wall-modeled large eddy simulation of supersonic combustion using flamelet/progress-variable modeling

Honest F. Mrema, Graham V. Candler

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Scopus citations


This paper presents the preliminary results of a research investigation intended to identify the most appropriate compressibility correction approach for the Flamelet Progress/Variable (FPV) formulation. This topic is vital for the design and advancement of hypersonic airbreathing vehicles. Consequently, there is a high demand for accurate, versatile, and computationally cost-effective methods for simulating supersonic combustion. This paper discusses the Flamelet Progress/Variable (FPV) formulation, which was utilized to simulate a reacting jet injection in a supersonic crossflow. The preliminary results presented in this paper are intended to show that the FPV formulation has been implemented in a well-established computational fluid dynamics (CFD) code. Additionally, we observed that the procedure to ignite the flow field in a FPV formulation is not trivial, and should be given more attention.

Original languageEnglish (US)
Title of host publication2018 Joint Propulsion Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105708
StatePublished - 2018
Event54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018 - Cincinnati, United States
Duration: Jul 9 2018Jul 11 2018

Publication series

Name2018 Joint Propulsion Conference


Conference54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018
Country/TerritoryUnited States

Bibliographical note

Funding Information:
This work was supported by a NASA Space Technology Research Fellowship.

Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics, Inc. All rights reserved.


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