Adjoint Formulation for an Embedded-Boundary Cartesian Method

Nemec, Marian; Aftosmis, Michael J.; Murman, Scott M.; Pulliam, Thomas H.

doi:10.2514/6.2005-877

Cited by 35 publications

(28 citation statements)

References 42 publications

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“…Cart3d is currently in use for large scale computations, including space shuttle ascent debris simulations [14]. Ongoing work continues in computing adjoints and shape sensitivities [15] and in novel ideas for moving beyond Euler calculations [16].…”

Section: Cut Cellsmentioning

confidence: 99%

A triangular cut-cell adaptive method for high-order discretizations of the compressible Navier–Stokes equations

Fidkowski

Darmofal

2007

Journal of Computational Physics

144

143

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Section: Cut Cellsmentioning

confidence: 99%

A triangular cut-cell adaptive method for high-order discretizations of the compressible Navier–Stokes equations

Fidkowski

Darmofal

2007

Journal of Computational Physics

144

143

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“…This method has been used extensively for sonic boom prediction and for low-boom design optimization [8][9][10]16]. More detail is available in previous publications [12,17,18]. …”

Section: A Nearfield Approachmentioning

confidence: 99%

Cart3D Simulations for the Second AIAA Sonic Boom Prediction Workshop

Anderson

Aftosmis

Nemec

2019

Journal of Aircraft

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Simulation results are presented for all test cases prescribed in the Second AIAA Sonic Boom Prediction Workshop. An inviscid, embedded-boundary Cartesian-mesh flow solver is used to compute "boom carpets"-pressure signatures at a range of specified distances and off-track angles. To accelerate the process, each boom carpet is automatically decomposed into several independent meshes, computed in parallel. Each mesh uses output-based mesh adaptation to affordably obtain credible results. This paper discusses improved Cartesian meshing strategies for boom prediction, including Mach alignment, azimuthal alignment, high-aspect-ratio cells, and adaptation functional weighting. The resulting nearfield signatures generally exhibit good convergence with mesh refinement. For an independent evaluation of our results, this study introduces a local error estimation procedure that highlights regions of the signatures most sensitive to mesh refinement. Results are also presented for the two atmospheric propagation test cases, which investigate the effects of atmospheric profiles on ground noise. Propagation is handled with an augmented Burgers' equation method (NASA's sBOOM), and ground noise metrics are compared.

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“…In this way, the mes h refinement procedure generates a mes h that reduces the discretization errors in the outputs so that the influence of these error on the output functional is below a specified error tolerance. A more complete analysis of the adjoint fo rmu lation and its applications on complex geometJies can be found in [8] and [9]. Another valuable capability of Cart3D is the abihty to ac hieve a user-requested value of CL by modifying the angle of attack at specified time steps.…”

Section: Computational Aerodynamic Toolsmentioning

confidence: 99%

Elastically Shaped Wing Optimization and Aircraft Concept for Improved Cruise Efficiency

Nguyen

Trinh

Reynolds

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Tbis paper presents the findings of a study conducted tn 2010 by the NASA Innovation Fund Award project entitled "Elastically Shaped Future Air Vehicle Concept" . The study presents three themes in support of meeting national and global aviation challenges of reducing fuel burn for present and future aviation sys tems. The first theme addresses tlle drag reduction goal tbrougb innovative vebicle configurations via non-planar wing optimization. Two wing candidate concepts bave been identified from tbe wing optimization: a drooped wing s bape and an inflected win g shape. The drooped wing shape is a truly biologically inspired wing concept that mimics a seagull wing and co uld acbieve about 5% to 6% drag reductio n, wbicb is aerodynamically significa nt. From a practical perspective, this concept would require new radical changes to the current aircraft development capabilities for new vehicles witb futuristiC-looking wings sucb as tbis concept. T be inflected wing concepts conld acbieve between 3% to 4% drag reduction . While the drag reductio n benefit may be les , tbe inflected-wing concept could bave a near-term impact si nce thi s concept could be developed within the current aircraft development capabilities. The second theme addresses the drag reducti on goa l through a new concept of elastic wing shaping control. By aeroelasticaUy tailoring tbe wing sbape with active control to mailltatn optimal aerodynamics, a sig nificant drag reduction benefit could be realized . A significant reduction in fuel burn for lo ng-range cruise from elastic wing sbaping control could be realized. To reali ze the potential of the elastic wi ng shaping control concept, the third theme emerges that addresses the drag reduction goal througb a new aerodynamic co ntrol effector called a variable camber continuou trailing edge flap. Conventional aerodynami c control surfaces are di screte independent surfaces that cause geometriC di sco ntinuities at the trailing edge region. These discontinuities promote vorticities which result in drag rises as well as noise sources. Tbe variable camber trailing edge flap concept could provide a substantial drag reduction benefi t over a co nventional discrete flap system. AerodynamiC simulations sbow a drag reduction of over 50% could be acbieved witb tbe flap concept over a conventional discrete flap sys tem.

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Adjoint Formulation for an Embedded-Boundary Cartesian Method

Cited by 35 publications

References 42 publications

A triangular cut-cell adaptive method for high-order discretizations of the compressible Navier–Stokes equations

A triangular cut-cell adaptive method for high-order discretizations of the compressible Navier–Stokes equations

Cart3D Simulations for the Second AIAA Sonic Boom Prediction Workshop

Elastically Shaped Wing Optimization and Aircraft Concept for Improved Cruise Efficiency

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