Computational study of high speed flow on a sliced cone-flap geometry

John Thome, John D. Reinert, Anubhav Dwivedi, Graham V. Candler

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

11 Scopus citations


A generic hypersonic vehicle configuration is studied from an in-depth computational standpoint to investigate high speed flow properties and explore future work regarding the stability properties of such a configuration. Geometries such as the Space Shuttle, X-15, ESA ixv, EXPERT, X-37b, and the HTV project are all real world examples of hypersonic configurations that utilize body flap control surfaces to maintain control authority. These projects provide the motivation for understanding the unassumingly complex state of the flow and provide a computational explanation for many of the features that are observed in experimental tests. This paper also presents quantitative comparisons against experimental surface pressure measurements and computational predictions as well as force coefficients for a large range of angles of attack.

Original languageEnglish (US)
Title of host publication2018 Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105531
StatePublished - 2018
Event48th AIAA Fluid Dynamics Conference, 2018 - Atlanta, United States
Duration: Jun 25 2018Jun 29 2018

Publication series

Name2018 Fluid Dynamics Conference


Other48th AIAA Fluid Dynamics Conference, 2018
Country/TerritoryUnited States

Bibliographical note

Funding Information:
The authors would like to thank Gregory McKiernan for providing experimental conditions of wind tunnel runs and private communications with the authors. This work was sponsored by the Air Force Office of Scientific Research Grant FA9550-17-1-0250 by the Collaborative Center for Aeronautical Sciences (CCAS). 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 AFOSR or the U.S. Government.

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


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