A status report is provided on the collaboration between the Royal Institute of Technology (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).
Computational Results for the KTH-NASA Wind-Tunnel Model Used for Acquisition of Transonic Nonlinear Aeroelastic Data
2017
19 pages
Report
No indication
English
Computer Software , Aircraft , Test Facilities & Equipment , Aeroelasticity , Computational fluid dynamics , Data acquisition , Design analysis , Fighter aircraft , Nonlinearity , Systems analysis , Transonic wind tunnels , Wind tunnel models , Wing profiles , Acceleration measurement , Dynamic modulus of elasticity , Finite element method , Fluid flow , International cooperation , Linearity , Reduced order filters , Strain measurement
British Library Conference Proceedings | 2016
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