TY - GEN
T1 - Unstructured grid simulations of transonic Shockwave-Boundary Layer Interaction-induced oscillations
AU - Bhamidipati, Keerti K.
AU - Reasor, Daniel A.
AU - Pasiliao, Crystal L.
N1 - Publisher Copyright:
© 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2015
Y1 - 2015
N2 - Shockwave oscillations at transonic freestream conditions on airfoil and wing models were simulated using unstructured computational fluid dynamics techniques. The models utilized either the OAT15A or NACA 64A204 airfoil profile. The node-based finite-volume solver developed by NASA’s Langley Research Center, FUN3D version 12.4, was employed. Mixed element type grids were constructed using the AFLR libraries integrated into the CREATE™-MG Capstone mesh generation software. The grids contained triangle elements on the airfoil/wing surface, prismatic elements in the boundary layer, and tetrahedral elements in the fluid domain. The work presented herein demonstrates that while unstructured grid URANS simulations are capable of predicting shockwave oscillations, frequency and damping of the oscillations are sensitive to numerous grid characteristics. Furthermore, results show that the inclusion of non-airfoil geometries in models does not significantly alter the primary shockwave oscilaltion frequency.
AB - Shockwave oscillations at transonic freestream conditions on airfoil and wing models were simulated using unstructured computational fluid dynamics techniques. The models utilized either the OAT15A or NACA 64A204 airfoil profile. The node-based finite-volume solver developed by NASA’s Langley Research Center, FUN3D version 12.4, was employed. Mixed element type grids were constructed using the AFLR libraries integrated into the CREATE™-MG Capstone mesh generation software. The grids contained triangle elements on the airfoil/wing surface, prismatic elements in the boundary layer, and tetrahedral elements in the fluid domain. The work presented herein demonstrates that while unstructured grid URANS simulations are capable of predicting shockwave oscillations, frequency and damping of the oscillations are sensitive to numerous grid characteristics. Furthermore, results show that the inclusion of non-airfoil geometries in models does not significantly alter the primary shockwave oscilaltion frequency.
UR - https://www.scopus.com/pages/publications/85088065100
U2 - 10.2514/6.2015-2287
DO - 10.2514/6.2015-2287
M3 - Conference contribution
AN - SCOPUS:85088065100
SN - 9781624103667
T3 - 22nd AIAA Computational Fluid Dynamics Conference
BT - 22nd AIAA Computational Fluid Dynamics Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 22nd AIAA Computational Fluid Dynamics Conference, 2015
Y2 - 22 June 2015 through 26 June 2015
ER -