The YF-12A aircraft, a delta-winged vehicle powered by two jet engines, was utilized in an investigation of the structural dynamic characteristics of a large, flexible, supersonic research vehicle. A large NASA structural analysis (NASTRAN) finite-element model was used to compute the ten lowest frequency symmetric and ten lowest frequency antisymmetric modes for the YF-12A aircraft. The results of the analysis were compared with experimental data obtained in a ground vibration test conducted with the completed aircraft. It was found that the finite-element structural model employed provides an adequate prediction of the dynamic behavior of the aircraft structure in the case of basic wing and body modes.
Results of NASTRAN modal analyses and ground vibration tests on the YF-12A airplane
Winter Annual Meeting ; 1975 ; Houston, TX
1975-11-01
Conference paper
No indication
English
Accuracy of results with NASTRAN modal synthesis
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