Vehicle-scale simulations of hypersonic flows using the MMT chemical kinetics model

Ross S. Chaudhry, Iain D. Boyd, Graham V. Candler

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

9 Scopus citations


The Modified Marrone-Treanor (MMT) chemical kinetics model has recently been developed for and implemented in CFD codes suitable for vehicle-scale simulation. The MMT model is based on ab-initio quantum chemistry data and it is designed for hypersonic flows in air. This work investigates the effect of chemical kinetics model on a simple geometry for a range of altitudes. A 10 cm sphere-cone geometry at 5000 m/s is considered, with an isothermal non-catalytic wall. The difference in stagnationpoint heat flux between the MMT and Park models is found to be up to 31 % for the recombination-dominated regime and up to 12 % for the dissociation-dominated regime. Qualitatively similar differences are also observed on the cone portion of the body, with up to a 18 % difference in area-averaged heat flux. Next, several modifications to the MMT model are tested, based on uncertainties and physical phenomena. Maximum differences in stagnation-point heat flux of about 5 % are observed when modifying the O2 + O dissociation rate, the rate of NO dissociation, and the approximate treatment of non-Boltzmann distributions. However, none of these realistic modifications approach the differences observed between the Park and MMT models, confirming these differences as significant. These results help to clarify the MMT model and decrease uncertainties by targeting future investigations.

Original languageEnglish (US)
Title of host publicationAIAA AVIATION 2020 FORUM
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105982
StatePublished - 2020
EventAIAA AVIATION 2020 FORUM - Virtual, Online
Duration: Jun 15 2020Jun 19 2020

Publication series

Volume1 PartF


CityVirtual, Online

Bibliographical note

Funding Information:
This work was sponsored by the Air Force Office of Scientific Research under grants FA9550-16-1-0291, FA9550-17-1-0250, and FA9550-19-1-0219. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the funding agencies or the U.S. Government.

Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.


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