TY - GEN
T1 - Immersed boundary method for compressible high-reynolds number viscous flow around moving bodies
AU - Cho, Yong
AU - Chopra, Jogesh
AU - Morris, Philip J.
N1 - Copyright:
Copyright 2020 Elsevier B.V., All rights reserved.
PY - 2007
Y1 - 2007
N2 - This paper describes a methodology for the simulation of high Reynolds number flow over rigid and moving bodies. The calculations are performed on a structured Cartesian grid regardless of the geometric complexity or motion of the body. The approach is based on a modified version of the Brinkman Penalization method. This paper describes the implementation of a simple modified penalization method for compressible flows. To avoid oscillations in the vicinity of the body and to simulate shock-containing flows, a Weighted Essentially Non-Oscillatory scheme is used to discretize the spatial flux derivatives. Two turbulence models are used: the two-equation Menter SST Unsteady Reynolds-averaged Navier-Stokes model and a two-equation Detached Eddy Simulation. The method is implemented for both stationary and moving grids in a three-dimensional parallel code. Results are given for a grid dependence study, flow over airfoils at subsonic, transonic and supersonic conditions, and unsteady transonic flow over a cylinder and an airfoil at high angle of attack. The effect of the choice of turbulence model is shown. The moving grid capability is demonstrated for airfoils at a high angles of attack and a cylinder rotating at high speed. Finally, as a larger scale demonstration, the flow around a rotor blade with an active flap is simulated.
AB - This paper describes a methodology for the simulation of high Reynolds number flow over rigid and moving bodies. The calculations are performed on a structured Cartesian grid regardless of the geometric complexity or motion of the body. The approach is based on a modified version of the Brinkman Penalization method. This paper describes the implementation of a simple modified penalization method for compressible flows. To avoid oscillations in the vicinity of the body and to simulate shock-containing flows, a Weighted Essentially Non-Oscillatory scheme is used to discretize the spatial flux derivatives. Two turbulence models are used: the two-equation Menter SST Unsteady Reynolds-averaged Navier-Stokes model and a two-equation Detached Eddy Simulation. The method is implemented for both stationary and moving grids in a three-dimensional parallel code. Results are given for a grid dependence study, flow over airfoils at subsonic, transonic and supersonic conditions, and unsteady transonic flow over a cylinder and an airfoil at high angle of attack. The effect of the choice of turbulence model is shown. The moving grid capability is demonstrated for airfoils at a high angles of attack and a cylinder rotating at high speed. Finally, as a larger scale demonstration, the flow around a rotor blade with an active flap is simulated.
UR - http://www.scopus.com/inward/record.url?scp=34250806084&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=34250806084&partnerID=8YFLogxK
U2 - 10.2514/6.2007-125
DO - 10.2514/6.2007-125
M3 - Conference contribution
AN - SCOPUS:34250806084
SN - 1563478900
SN - 9781563478901
T3 - Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
SP - 1413
EP - 1426
BT - Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 45th AIAA Aerospace Sciences Meeting 2007
Y2 - 8 January 2007 through 11 January 2007
ER -