Computational results for the KTH-NASA wind-tunnel model used for acquisition of transonic nonlinear aeroelastic data Show others and affiliations
2017 (English) In: 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2017, American Institute of Aeronautics and Astronautics Inc, AIAA , 2017Conference paper, Published paper (Refereed)
Abstract [en]
A status report is provided on the collaboration between the Royal Institute of Tech- nology (KTH) in Sweden and the NASA Langley Research Center regarding the aeroelastic analyses of a full-span fighter configuration wind-tunnel model. This wind-tunnel model was tested in the Transonic Dynamics Tunnel (TDT) in the summer of 2016. Large amounts of data were acquired including steady/unsteady pressures, accelerations, strains, and measured dynamic deformations. The aeroelastic analyses presented include linear aeroelastic analyses, CFD steady analyses, and analyses using CFD-based reduced-order models (ROMs).
Place, publisher, year, edition, pages American Institute of Aeronautics and Astronautics Inc, AIAA , 2017.
Keywords [en]
Aeroelasticity, Aircraft models, Data reduction, NASA, Structural dynamics, Supersonic aircraft, Transonic aerodynamics, Aeroelastic analysis, Computational results, Fighter configuration, Large amounts of data, NASA Langley Research Center, Reduced order models, Transonic dynamics tunnels, Wind tunnel modeling, Wind tunnels
National Category
Vehicle and Aerospace Engineering Vehicle and Aerospace Engineering
Identifiers URN: urn:nbn:se:kth:diva-302183 DOI: 10.2514/6.2017-1814 Scopus ID: 2-s2.0-85088759076 ISBN: 9781624104534 (print) OAI: oai:DiVA.org:kth-302183 DiVA, id: diva2:1597869
Conference 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2017, 9 January 2017 through 13 January 2017
Note QC 20220301
2021-09-282021-09-282026-03-12 Bibliographically approved