Results of NASTRAN modal analyses and ground vibration tests on the YF-12A airplaneThe 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.
Document ID
19760038889
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kordes, E. E. (NASA Flight Research Center Edwards, Calif., United States)
Curtis, A. R. (Lockheed-California Co. Burbank, Calif., United States)
Date Acquired
August 8, 2013
Publication Date
November 1, 1975
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
ASME PAPER 75-WA/AERO-8
Meeting Information
Meeting: Winter Annual Meeting
Location: Houston, TX
Start Date: November 30, 1975
End Date: December 4, 1975
Sponsors: American Society of Mechanical Engineers