TY - GEN
T1 - A continuous adjoint method for unstructured grids
AU - Jameson, Antony
AU - Sriram,
AU - Martinelli, Luigi
PY - 2003
Y1 - 2003
N2 - Adjoint based shape optimization methods have proven to be computationally efficient for aerodynamic problems. The majority of the studies on adjoint methods have used structured grids to discretize the computational domain. Due to the potential advantages of unstructured grids for complex configurations, in this study we have developed and validated a continuous adjoint formulation for unstructured grids. The hurdles posed in the computation of the gradient for unstructured grids are resolved by using a reduced gradient formulation. Methods to impose thickness constraints on unstructured grids are also discussed. Results for two and three dimensional simulations of airfoils and wings in transonic flow are used to validate the design procedure. Finally, the design procedure is applied to redesign the shape of a transonic business jet configuration, and we were able to reduce the drag of the aircraft from 235 to 216 counts resulting in a shock free wing.
AB - Adjoint based shape optimization methods have proven to be computationally efficient for aerodynamic problems. The majority of the studies on adjoint methods have used structured grids to discretize the computational domain. Due to the potential advantages of unstructured grids for complex configurations, in this study we have developed and validated a continuous adjoint formulation for unstructured grids. The hurdles posed in the computation of the gradient for unstructured grids are resolved by using a reduced gradient formulation. Methods to impose thickness constraints on unstructured grids are also discussed. Results for two and three dimensional simulations of airfoils and wings in transonic flow are used to validate the design procedure. Finally, the design procedure is applied to redesign the shape of a transonic business jet configuration, and we were able to reduce the drag of the aircraft from 235 to 216 counts resulting in a shock free wing.
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M3 - Conference contribution
AN - SCOPUS:84897585067
SN - 9781624100864
T3 - 16th AIAA Computational Fluid Dynamics Conference
BT - 16th AIAA Computational Fluid Dynamics Conference
T2 - 16th AIAA Computational Fluid Dynamics Conference 2003
Y2 - 23 June 2003 through 26 June 2003
ER -