CFD simulations of the supersonic inflatable aerodynamic decelerator (SIAD) ballistic range tests

Joseph M. Brock, Eric C. Stern, Michael C. Wilder

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

6 Scopus citations


A series of ballistic range tests were performed on a scaled model of the Supersonic Flight Demonstration Test (SFDT) intended to test the Supersonic Inflatable Aerodynamic Decelerator (SIAD) geometry. The purpose of these experiments were to provide aerodynamic coefficients of the vehicle to aid in mission and vehicle design. The experimental data spans the moderate Mach number range, 3:8-2:0, with a total angle of attack (αT) range, 10°-20°. These conditions are intended to span the Mach-α space for the majority of the SFDT experiment. In an effort to validate the predictive capabilities of Computational Fluid Dynamics (CFD) for free-flight aerodynamic behavior, numerical simulations of the ballistic range experiment are performed using the unstructured finite volume Navier-Stokes solver, US3. D. Comparisons to raw vehicle attitude, and post-processed aerodynamic coefficients are made between simulated results and experimental data. The resulting comparisons for both raw model attitude and derived aerodynamic coefficients show good agreement with experimental results. Additionally, near body pressure field values for each trajectory simulated are investigated. Extracted surface and wake pressure data gives further insights into dynamic/flow coupling leading to a potential mechanism for dynamic instability.

Original languageEnglish (US)
Title of host publicationAIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)9781624104473
StatePublished - 2017
Event55th AIAA Aerospace Sciences Meeting - Grapevine, United States
Duration: Jan 9 2017Jan 13 2017

Publication series

NameAIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting


Other55th AIAA Aerospace Sciences Meeting
Country/TerritoryUnited States

Bibliographical note

Funding Information:
The primary author is supported through the NASA Entry Systems Modeling (ESM) project within the NASA Game Changing Development Program. Contract support was provided through AMA inc. under the NNA15BB15C contract. Eric Stern is supported through the NASA Engineering and Safety Center (NESC) Early Career Engineer program. The authors gratefully acknowledge Michael Barnhadt, Cole Kazemba, and Jeffrey Brown for their insight into various aspects of this work.

Publisher Copyright:
© 2017 by the American Institute of Aeronautics and Astronautics, Inc.


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