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dc.rights.licenseCopyright © 2019 by Carlos Lozanoes
dc.contributor.authorLozano, Carloses
dc.date.accessioned2023-12-04T09:36:53Z-
dc.date.available2023-12-04T09:36:53Z-
dc.date.issued2019-08-05-
dc.identifier.citationAIAA Journal 57(9): (2019)es
dc.identifier.otherhttps://arc.aiaa.org/doi/10.2514/1.J057259es
dc.identifier.urihttp://hdl.handle.net/20.500.12666/907-
dc.descriptionCopyright © 2019 by Carlos Lozano. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.es
dc.description.abstractIt has been long known that 2D and 3D inviscid adjoint solutions are generically singular at sharp trailing edges. In this paper, a concurrent effect is described by which wall boundary values of 2D and 3D inviscid continuous and discrete adjoint solutions based on lift and drag are strongly mesh dependent and do not converge as the mesh is refined. Various numerical tests are performed to characterize the problem. Lift-based adjoint solutions are found to be affected for any flow condition, whereas drag-based adjoint solutions are affected for transonic lifting flows. A (laminar) viscous case is examined as well, but no comparable behavior is found, which suggests that the issue is exclusive to inviscid flows. It is argued that this behavior is caused by the trailing edge adjoint singularity.es
dc.description.sponsorshipThe research described in this paper has been supported by INTA and the Ministry of Defence under the grant Termofluidodinámica (IGB99001). The author would like to thank J. Ponsin and D. Ekelschot for discussions. The computations reported in the paper were carried out with the TAU Code, developed at DLR’s Institute of Aerodynamics and Flow Technology at Göttingen and Braunschweig, which is licensed to INTA through a research and development cooperation agreement. Cross-checking has been also performed with the SU2 code, an open source code developed at the Aerospace Department of Stanford University.es
dc.language.isoenges
dc.publisherAerospace Research Centrales
dc.subjectTrailing edgeses
dc.subjectFlow conditionses
dc.subjectAirfoil profileses
dc.subjectAngle of attackes
dc.subjectPressure coefficientes
dc.subjectAerodynamic designes
dc.subjectEuler equationses
dc.subjectViscosityes
dc.subjectStagnation streamlineses
dc.subjectVortex sheddinges
dc.titleWatch your adjoints! Lack of mesh convergence in inviscid adjoint solutionses
dc.typeinfo:eu-repo/semantics/articlees
dc.identifier.doi10.2514/1.J057259-
dc.identifier.e-issn1533-385X-
dc.contributor.funderInstituto Nacional de Técnica Aeroespacial (INTA)es
dc.description.peerreviewedPeerreviewes
dc.type.hasVersioninfo:eu-repo/semantics/acceptedVersiones
dc.rights.accessRightsinfo:eu-repo/semantics/restrictedAccesses
dc.type.coarhttp://purl.org/coar/resource_type/c_6501es
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