Dynamic, viscous, free-To-oscillate simulations of the Mars Entry Atmospheric Data System (MEADS) ballistic range model are performed using two different flow solvers, OVERFLOW and US3D. At the time of publication, data from the ballistic range experiment was not yet available, so the current work serves as a code-To-code exercise. Results from the analysis show good agreement between the predicted static aerodynamic coefficients for each solver. Both codes predict damped pitch oscillations for Mach 3:0 with initial amplitudes of 5° and 30°, as well as for Mach 1:5 with initial amplitude of 30°. The two solvers predict undamped pitch oscillations for Mach 1:5 with initial amplitude of 5°. For most cases, US3D predicts less damping than OVERFLOW. The difference is attributed to higher pressures in the separated region of the wake, and the resultant effect on the backshell contribution to the pitching moment.
|Original language||English (US)|
|State||Published - 2016|
|Event||AIAA Atmospheric Flight Mechanics Conference, 2016 - San Diego, United States|
Duration: Jan 4 2016 → Jan 8 2016
|Other||AIAA Atmospheric Flight Mechanics Conference, 2016|
|Period||1/4/16 → 1/8/16|
Bibliographical noteFunding Information:
This work is supported through the NASA Engineering and Safety Center (NESC) Early Career Engineer Program. Additional support provided by the Entry Systems Modeling (ESM) project within NASA’s Game Changing Development Program. Mr. Brock is supported through NASA contract NNA15BB15C to AMA Inc.. The authors gratefully acknowledge Dr. Joseph Schulz and Dr. Michael Barnhardt for there helpful comments on the manuscript.
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