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OVERFLOW Analysis of Supersonic Retropropulsion Testing on a Blunt Mars Entry Vehicle ConceptSupersonic retropropulsion (SRP) flow over a Hypersonic Inflatable Aerodynamic Decelerator (HIAD) blunt-body vehicle was simulated using the Overflow Computational Fluid Dynamics (CFD) solver. Two nozzle configurations were tested (1E and 1F) as a subset of the seven total configurations in the Descent System Study (DSS) testing campaign. A generalized, Adaptive Mesh Refinement (AMR) shock capturing and plume refinement technique was developed and calibrated for producing automatic and unique grid systems optimized for any given testing condition. Solution independence from grid resolution was determined by successively increasing grid refinement until asymptotic convergence of the mean aerodynamic loads was observed. Overflow Reynolds-averaged Navier-Stokes (RANS) solutions produced realistic SRP flow phenomena, including Mach disk normal shocks contained in high-thrust plumes and bow shock triple-points. Solutions for the 1E nozzle configuration were steady. Conversely, a subset of the 1F test conditions were unsteady and exhibited periodic, non-sinusoidal expansions and contractions of the streamwise-oriented plume, resulting in unsteady aerodynamic loads on the vehicle. Initial investigations into the effect of turbulence modeling fidelity demonstrated significant differences between the aerodynamic loads simulated with RANS and Detached Eddy Simulation (DES). Multiple flow mechanisms were identified as root causes of these differences, including bow shock shape augmentation and reduced entrainment due to reduced turbulence in the DES simulations. Initial comparisons of pitching moment control authority and aerodynamic drag performance between the tested nozzle configurations demonstrated that the 1E configuration may be more advantageous for the Mars Entry, Descent, and Landing (EDL) task.
Document ID
20210025107
Acquisition Source
Ames Research Center
Document Type
Presentation
Authors
L. D. Halstrom
(Ames Research Center Mountain View, California, United States)
T. H. Pulliam
(Science and Technology Corporation (United States) Hampton, Virginia, United States)
R. E. Childs
(Science and Technology Corporation (United States) Hampton, Virginia, United States)
P. M. Stremel
(Science and Technology Corporation (United States) Hampton, Virginia, United States)
Date Acquired
November 29, 2021
Subject Category
Aerodynamics
Spacecraft Propulsion And Power
Meeting Information
Meeting: 2022 AIAA SciTech Forum
Location: San Diego, CA
Country: US
Start Date: January 3, 2022
End Date: January 7, 2022
Sponsors: American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 335803.04.21.21
CONTRACT_GRANT: NNA16BD60C
Distribution Limits
Public
Copyright
Portions of document may include copyright protected material.
Technical Review
NASA Peer Committee
Keywords
Supersonic Retropropulsion
Hypersonic Inflatable Aerodynamic Decelerator
OVERFLOW
CFD
EDL
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