The complete discrete adjoint equations for an unstructured finite volume compressible Navier-Stokes solver are discussed with respect to the memory and time efficient evaluation of their residuals, and their solution. It is seen that application of existing iteration methods for the non-linear equation - suitably adjointed - have a property of guaranteed convergence provided that the nonlinear iteration is well behaved. For situations where this is not the case, a stabilization method based on the Recursive Projection Method is developed. The resulting adjoint solver is applied to 3D optimization of a turbulent wing-fuselage configuration, as well as to goal-oriented adaptation using an error representation formula
A systematic methodology for formulating, implementing, solving and verifying discrete adjoint of th...
This paper presents the development of a fully implicit, low-memory discrete-adjoint method by means...
An overview of twenty years of adjoint-based aerodynamic design research at NASA Langley Research Ce...
The complete discrete adjoint equations for an unstructured finite volume compressible Navier-Stokes...
The complete discrete adjoint equations for an unstructured finite volume compressible Navier–Stokes...
A discrete adjoint method is developed and demonstrated for aerodynamic design optimization on unstr...
The solution of the discrete adjoint equations for an unstructured finite vol-ume compressible Navie...
Methods and computing hardware advances have enabled accurate predictions of complex compressible tu...
A discrete adjoint method is developed and demonstrated for aerodynamic design optimization on unstr...
Methods and computing hardware advances have enabled accurate predictions of complex compressible tu...
High-order methods have the potential to achieve higher accuracy at lower cost than lower order meth...
High-order methods have the potential to achieve higher accuracy at lower cost than lower order meth...
Aerospace industry is increasingly relying on advanced numerical flow simulation tools in the early ...
This paper explains how the solutions of appropriate adjoint equations can be used to estimate the e...
Shape optimization of modern three-dimensional hypersonic inlets requires many geometric design para...
A systematic methodology for formulating, implementing, solving and verifying discrete adjoint of th...
This paper presents the development of a fully implicit, low-memory discrete-adjoint method by means...
An overview of twenty years of adjoint-based aerodynamic design research at NASA Langley Research Ce...
The complete discrete adjoint equations for an unstructured finite volume compressible Navier-Stokes...
The complete discrete adjoint equations for an unstructured finite volume compressible Navier–Stokes...
A discrete adjoint method is developed and demonstrated for aerodynamic design optimization on unstr...
The solution of the discrete adjoint equations for an unstructured finite vol-ume compressible Navie...
Methods and computing hardware advances have enabled accurate predictions of complex compressible tu...
A discrete adjoint method is developed and demonstrated for aerodynamic design optimization on unstr...
Methods and computing hardware advances have enabled accurate predictions of complex compressible tu...
High-order methods have the potential to achieve higher accuracy at lower cost than lower order meth...
High-order methods have the potential to achieve higher accuracy at lower cost than lower order meth...
Aerospace industry is increasingly relying on advanced numerical flow simulation tools in the early ...
This paper explains how the solutions of appropriate adjoint equations can be used to estimate the e...
Shape optimization of modern three-dimensional hypersonic inlets requires many geometric design para...
A systematic methodology for formulating, implementing, solving and verifying discrete adjoint of th...
This paper presents the development of a fully implicit, low-memory discrete-adjoint method by means...
An overview of twenty years of adjoint-based aerodynamic design research at NASA Langley Research Ce...