@conference {Carson_2020_MOESS_CG_DG,
	title = {Mesh optimization via error sampling and synthesis: An update},
	booktitle = {AIAA conference paper},
	number = {2020-0087},
	year = {2020},
	doi = {10.2514/6.2020-0087},
	author = {Hugh A. Carson and Arthur C. Huang and Marshall C. Galbraith and Steven R. Allmaras and David L. Darmofal}
}
@conference {Huang_2020_Variational,
	title = {A Variational multiscale method with discontinuous subscales for output-based adaptation of aerodynamic flows},
	booktitle = {AIAA conference paper},
	number = {2020-1563},
	year = {2020},
	doi = {10.2514/6.2020-1563},
	author = {Arthur C. Huang and Hugh A. Carson and Steven R. Allmaras and Marshall C. Galbraith and David L. Darmofal and Dimitry S. Kamenetskiy}
}
@article {Jayasinghe_2019_Distributed_Well_Model,
	title = {A discretization-independent distributed well model},
	journal = {Society of Petroleum Engineers Journal},
	year = {2019},
	month = {October},
	doi = {10.2118/198898-PA},
	author = {Jayasinghe, S. and Darmofal, D.L. and Dow, E. and Galbraith, M.C. and Allmaras, S.R.}
}
@conference {Caplan_2019_Extension_of_local_cavity_operators_to_3dt_spacetime_mesh_adaptation,
	title = {{Extension of local cavity operators to 3d+t spacetime mesh adaptation}},
	booktitle = {AIAA conference paper},
	number = {2019-1992},
	year = {2019},
	doi = {10.2514/6.2019-1992},
	author = {Caplan, P.C. and Haimes, R. and Darmofal, D.L. and Galbraith, M.C.}
}
@conference {Drela_2019_hybrid_shell_model,
	title = {Hybrid shell model for aeroelastic modeling},
	booktitle = {AIAA conference paper},
	number = {2019{\textendash}2227},
	year = {2019},
	type = {AIAA Paper},
	doi = {10.2514/6.2019-2227},
	author = {Mark Drela and Marshall Galbraith and Robert Haimes and Steven R. Allmaras and David L. Darmofal}
}
@conference {Zhang_2019_IBL2_free_transition,
	title = {A strongly-coupled non-parametric integral boundary layer method for aerodynamic analysis with free transition},
	booktitle = {AIAA conference paper},
	number = {2019-1154},
	year = {2019},
	doi = {10.2514/6.2019-1154},
	author = {Zhang, Shun and Drela, Mark and Allmaras, Steven R. and Galbraith, Marshall C. and Darmofal, David L.}
}
@conference {Park_2019_Verification_of_Unstructured_Grid_Adaptation_Components,
	title = {Verification of unstructured grid adaptation components},
	booktitle = {AIAA conference paper},
	number = {2019{\textendash}1723},
	year = {2019},
	type = {AIAA Paper},
	doi = {10.2514/6.2019-1723},
	author = {Michael A. Park and Aravind Balan and W. Kyle Anderson and Marshall C. Galbraith and Philip Claude Caplan and Hugh A. Carson and Todd Michal and Joshua A. Krakos and Dmitry S. Kamenetskiy and Adrien Loseille and Fr{\'e}d{\'e}ric Alauzet and Lo{\"\i}c Frazza and Nicolas Barral}
}
@article {Jayasinghe_2018_Adjoint_Analysis_BuckleyLeverett_TwoPhase,
	title = {Adjoint analysis of Buckley-Leverett and two-phase flow equations},
	journal = {Computational Geosciences},
	volume = {22},
	number = {2},
	year = {2018},
	month = {April},
	pages = {527{\textendash}542},
	author = {Jayasinghe, Savithru and Darmofal, David L. and Galbraith, Marshall C. and Burgess, Nicholas K. and Allmaras, Steven R.}
}
@conference {Galbraith_2018_SANS_RANS_3D_Benchmark,
	title = {SANS RANS solutions for 3D benchmark configurations},
	booktitle = {AIAA conference paper},
	number = {2018{\textendash}1570},
	year = {2018},
	type = {AIAA Paper},
	doi = {10.2514/6.2018-1570},
	author = {Marshall C. Galbraith and Steven R. Allmaras and David L. Darmofal}
}
@article {Jayasinghe_2017_Spacetime_Adaptive_Method_Reservoir_Flows_Formulation,
	title = {A space-time adaptive method for reservoir flows: Formulation and one-dimensional application},
	journal = {Computational Geosciences},
	volume = {22},
	year = {2018},
	month = {02/2018},
	pages = {107-123},
	chapter = {107},
	abstract = {<p>This paper presents a space-time adaptive framework for solving porous media flow problems, with specific application to reservoir simulation. A fully unstructured mesh discretization of space and time is used instead of a conventional time-marching approach. A space-time discontinuous Galerkin finite element method is employed to achieve a high-order discretization on the anisotropic, unstructured meshes. Anisotropic mesh adaptation is performed to reduce the error of a specified output of interest, by using a posteriori error estimates from the dual-weighted residual method to drive a metric-based mesh optimization algorithm. The space-time adaptive method is tested on a one-dimensional two-phase flow problem, and is found to be more efficient in terms of computational cost (degrees-of-freedom and total runtime) required to achieve a specified output error level, when compared to a conventional first-order time-marching finite volume method and the space-time discontinuous Galerkin method on structured meshes.</p>
},
	issn = {1573-1499},
	doi = {10.1007/s10596-017-9673-9},
	url = {http://dx.doi.org/10.1007/s10596-017-9673-9},
	author = {Jayasinghe, Y S and Darmofal, D L and Burgess, N K and Galbraith, M C and Allmaras, S R}
}
@conference {Huang_2019_Wellposed_NS_BCs,
	title = {Well-posed subsonic inflow/outflow boundary conditions for the Navier-Stokes equations},
	booktitle = {AIAA conference paper},
	number = {2018{\textendash}0361},
	year = {2018},
	type = {AIAA Paper},
	doi = {10.2514/6.2018-0361},
	author = {Arthur C. Huang and Steven R. Allmaras and Marshall C. Galbraith and David L. Darmofal}
}
@article {Carson_2017_ErrorEstimation,
	title = {Analysis of output-based error estimation for finite element methods},
	journal = {Applied Numerical Mathematics},
	volume = {118},
	year = {2017},
	pages = {182 - 202},
	abstract = {Abstract In this paper, we develop a priori estimates for the convergence of outputs, output error estimates, and localizations of output error estimates for Galerkin finite element methods. Output error estimates for order p finite element solutions are constructed using the Dual-Weighted Residual (DWR) method with a higher-order p ' \&gt; p dual solution. Specifically, we analyze these \{DWR\} estimates for Continuous Galerkin (CG), Discontinuous Galerkin (DG), and Hybridized \{DG\} (HDG) methods applied to the Poisson problem. For all discretizations, as h {\textrightarrow} 0 , we prove that the output and output error estimate converge at order 2p and 2 p ' (assuming sufficient smoothness), while localizations of the output and output error estimate converge at 2 p + d and p + p ' + d . For DG, the results use a new post processing for the error associated with the lifting operator. For HDG, these rates improve an additional order when the stabilization is based upon an O ( 1 ) length scale.},
	keywords = {Hybridizable Discontinuous Galerkin},
	issn = {0168-9274},
	doi = {http://dx.doi.org/10.1016/j.apnum.2017.03.004},
	url = {http://www.sciencedirect.com/science/article/pii/S0168927417300648},
	author = {Carson, H A and Darmofal, D L and Galbraith, M C and Allmaras, S R}
}
@article {Caplan_2017_Anisotropic_geometryconforming_dsimplicial_meshing_via_isometric_embeddings,
	title = {Anisotropic Geometry-Conforming d-simplicial Meshing via Isometric Embeddings},
	journal = {Procedia Engineering},
	volume = {203},
	year = {2017},
	note = {26th International Meshing Roundtable},
	pages = {141-153},
	publisher = {Springer Berlin Heidelberg},
	author = {Caplan, P.C. and Haimes, R. and Darmofal, D.L. and Galbraith, M.C.}
}
@conference {Couchman_2017_FEMweakconvergence,
	title = {On the convergence of higher-order finite element methods to weak solutions},
	booktitle = {AIAA conference paper},
	number = {2017-4274},
	year = {2017},
	keywords = {finite element methods},
	doi = {10.2514/6.2017-4274},
	author = {Couchman, B L and Darmofal, D L and Allmaras, S R and Galbraith, M C}
}
@conference {Zhang_2017_IBL_DG,
	title = {A non-parametric discontinuous Galerkin formulation of the integral boundary layer equations with strong viscous/inviscid coupling},
	booktitle = {AIAA conference paper},
	number = {2017-4278},
	year = {2017},
	keywords = {finite element methods, integral boundary layer methods},
	doi = {10.2514/6.2017-4278},
	author = {Zhang, S and Galbraith, M C and Allmaras, S R and Drela, M and Darmofal, D L}
}
@article {Hu_2016_turbmodelcases_AIAAJ,
	title = {Application of Higher-order Adaptive Method to Reynolds-Averaged Navier{\textendash}Stokes Test Cases},
	journal = {AIAA Journal},
	volume = {54},
	number = {9},
	year = {2016},
	doi = {10.2514/1.J054558},
	author = {Hu, Y and Wagner, C F and Allmaras, S R and Galbraith, M C and Darmofal, D L}
}
@conference {Galbraith_2015_Verification_CFD_Development,
	title = {A verification driver process for rapid development of CFD software},
	booktitle = {AIAA conference paper},
	number = {2015-0818},
	year = {2015},
	doi = {10.2514/6.2015-0818},
	author = {Galbraith, M C, and Allmaras, S R, and Darmofal, D L}
}
@booklet {Vision_2030_Final_Report_CRDL,
	title = {CFD Vision 2030 Study: A Path to Revolutionary Computational Aerosciences},
	journal = {NASA Technical Report},
	number = {NASA/CR-2014-218178},
	year = {2014},
	author = {Slotnick, J P and Khodadoust, A and Alonso, J J and Darmofal, D L and Gropp, W D and Lurie, E A and Mavriplis, D J}
}
@article {Slotnick_2014_EnivornmentCFD,
	title = {Enabling the environmentally clean air transportation of the future: a vision of computational fluid dynamics in 2030},
	journal = {Philosophical transactions. Series A, Mathematical, physical, and engineering sciences},
	volume = {372},
	number = {2022},
	year = {2014},
	month = {08},
	pages = {20130317},
	abstract = {As global air travel expands rapidly to meet demand generated by economic growth, it is essential to continue to improve the efficiency of air transportation to reduce its carbon emissions and address concerns about climate change. Future transports must be {\textquoteleft}cleaner{\textquoteright}and designed to include technologies that will continue to lower engine emissions and reduce community noise. The use of computational fluid dynamics (CFD) will be critical to enable the design of these new concepts. In general, the ability to simulate aerodynamic and reactive flows using CFD has progressed rapidly during the past several decades and has fundamentally changed the aerospace design process. Advanced simulation capabilities not only enable reductions in ground-based and flight-testing requirements, but also provide added physical insight, and enable superior designs at reduced cost and risk. In spite of considerable success, reliable use of CFD has remained confined to a small region of the operating envelope due, in part, to the inability of current methods to reliably predict turbulent, separated flows. Fortunately, the advent of much more powerful computing platforms provides an opportunity to overcome a number of these challenges. This paper summarizes the findings and recommendations from a recent NASA-funded study that provides a vision for CFD in the year 2030, including an assessment of critical technology gaps and needed development, and identifies the key CFD technology advancements that will enable the design and development of much cleaner aircraft in the future.},
	isbn = {1364-503X; 1471-2962},
	doi = {10.1098/rsta.2013.0317},
	url = {http://www.ncbi.nlm.nih.gov/pmc/articles/PMC4095895/},
	author = {Slotnick, J P and Khodadoust, A and Alonso, J J and Darmofal, D L and Gropp, W D and Lurie, E A and Mavriplis, D J and Venkatakrishnan, V}
}
@article {Garzon_2003_ImpactGeometricVariabilityCompressor,
	title = {Impact of geometric variability on axial compressor performance},
	journal = {Journal of Turbomachinery},
	volume = {125},
	number = {4},
	year = {2003},
	pages = {692{\textendash}703},
	abstract = {A probabilistic methodology to quantify the impact of geometric variability on compressor aerodynamic performance is presented. High-fidelity probabilistic models of geometric variability are derived using a principal-component analysis of blade surface measurements. This probabilistic blade geometry model is then combined with a compressible, viscous blade-passage analysis to estimate the impact on the passage loss and turning using a Monte Carlo simulation. Finally, a mean-line multistage compressor model, with probabilistic loss and turning models from the blade-passage analysis, is developed to quantify the impact of the blade variability on overall compressor efficiency and pressure ratio. The methodology is applied to a flank-milled integrally bladed rotor. Results demonstrate that overall compressor efficiency can be reduced by approximately 1{\%} due to blade-passage effects arising from representative manufacturing variability.},
	isbn = {0889-504X},
	doi = {10.1115/1.1622715},
	author = {Garzon, V E and Darmofal, D L}
}
@mastersthesis {Garzon_2003_Phd,
	title = {Probabilistic Aerothermal Design of Compressor Airfoils},
	year = {2003},
	school = {Massachusetts Institute of Technology},
	type = {phd},
	address = {Department of Aeronautics and Astronautics},
	url = {http://hdl.handle.net/1721.1/16995},
	author = {Garzon, V E}
}
@article {Darmofal_2001_VortexCore1DModel,
	title = {Vortex core behaviour in confined and unconfined geometries: A quasi-one-dimensional model},
	journal = {Journal of Fluid Mechanics},
	volume = {449},
	year = {2001},
	pages = {61{\textendash}84},
	doi = {10.1017/S0022112001006103},
	author = {Darmofal, D L and Khan, R and Greitzer, E M and Tan, C S}
}
@article {Darmofal_2000_BC_1DPCEuler,
	title = {Eigenmode Analysis of Boundary Conditions for the One-Dimensional Preconditioned Euler Equations},
	journal = {Journal of Computational Physics},
	volume = {160},
	number = {1},
	year = {2000},
	pages = {369 - 384},
	abstract = {The effect of local preconditioning on boundary conditions is analyzed for the subsonic, one-dimensional Euler equations. Decay rates for the eigenmodes of the initial boundary value problem are determined for different boundary conditions and different preconditioners whose intent is to accelerate low Mach number computations. Riemann invariant boundary conditions based on the unpreconditioned Euler equations are shown to be reflective when used with preconditioning, and asymptotically, at low Mach numbers, initial disturbances do not decay. Other boundary conditions are shown to be perfectly nonreflective in conjunction with preconditioning. Two-dimensional numerical results confirm the trends predicted by the one-dimensional analysis.},
	issn = {0021-9991},
	doi = {10.1006/jcph.2000.6472},
	url = {http://www.sciencedirect.com/science/article/pii/S0021999100964726},
	author = {Darmofal, D L and Moinier, P and Giles, M B}
}
@booklet {Haimes_1991_VKI,
	title = {Visual3 - A software environment for flow visualization},
	journal = {VKI Lecture Series on Computer Graphics and Flow Visualization in CFD},
	year = {1991},
	keywords = {scientific visualization},
	author = {Haimes, R and Giles, M B and Darmofal, D L}
}
