TY - GEN
T1 - Computational analysis of turbulent internal flow in ballistic solid rocket motors
AU - Arabshahi, Abdollah
AU - Sreenivas, Kidambi
AU - Nichols, D. Stephen
AU - Mitchell, Brent C.J.
AU - Taylor, Lafayette K.
AU - Whitfield, David L.
PY - 2007
Y1 - 2007
N2 - The present study was undertaken to provide a computational analysis tool in support of modeling and simulation of solid rocket motors by the Air Force Research Laboratory (AFRL). The need to establish a predictive capability for the detailed three-dimensional turbulent flow within solid rocket motors presented an opportunity to apply two in-house families of structured-grid and unstructured-grid compressible Navier-Stokes flow solvers which have evolved over many years. The solvers utilize a state-of-the-art implicit upwind numerical scheme to solve the time-dependent Navier-Stokes equations in either a Cartesian (unstructured) or a generalized time-dependent curvilinear coordinate system (structured). Computational results have been obtained for two experimental cold-flow cases during the course of this work. These cases serve as baselines for comparison to demonstrate the capability of the flow solvers to simulate solid rocket motor flows. The present flow solvers give promising results for flow field predictions in regimes ranging from low subsonic to supersonic within the rocket motor system.
AB - The present study was undertaken to provide a computational analysis tool in support of modeling and simulation of solid rocket motors by the Air Force Research Laboratory (AFRL). The need to establish a predictive capability for the detailed three-dimensional turbulent flow within solid rocket motors presented an opportunity to apply two in-house families of structured-grid and unstructured-grid compressible Navier-Stokes flow solvers which have evolved over many years. The solvers utilize a state-of-the-art implicit upwind numerical scheme to solve the time-dependent Navier-Stokes equations in either a Cartesian (unstructured) or a generalized time-dependent curvilinear coordinate system (structured). Computational results have been obtained for two experimental cold-flow cases during the course of this work. These cases serve as baselines for comparison to demonstrate the capability of the flow solvers to simulate solid rocket motor flows. The present flow solvers give promising results for flow field predictions in regimes ranging from low subsonic to supersonic within the rocket motor system.
UR - http://www.scopus.com/inward/record.url?scp=34347232682&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:34347232682
SN - 1563478900
SN - 9781563478901
T3 - Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
SP - 17026
EP - 17035
BT - Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
T2 - 45th AIAA Aerospace Sciences Meeting 2007
Y2 - 8 January 2007 through 11 January 2007
ER -