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Flight and analytical investigations of a structural mode excitation system on the YF-12A airplaneA structural excitation system, using an oscillating canard vane to generate force, was mounted on the forebody of the YF-12A airplane. The canard vane was used to excite the airframe structural modes during flight in the subsonic, transonic, and supersonic regimes. Structural modal responses generated by the canard vane forces were measured at the flight test conditions by airframe-mounted accelerometers. Correlations of analytical and experimental aeroelastic results were made. Doublet lattice, steady state double lattice with uniform lag, Mach box, and piston theory all produced acceptable analytical aerodynamic results within the restrictions that apply to each. In general, the aerodynamic theory methods, carefully applied, were found to predict the dynamic behavior of the YF-12A aircraft adequately.
Document ID
19870013252
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Goforth, E. A. (Lockheed-California Co. Burbank, CA, United States)
Murphy, R. C. (Lockheed-California Co. Burbank, CA, United States)
Beranek, J. A. (Lockheed-California Co. Burbank, CA, United States)
Davis, R. A. (Lockheed-California Co. Burbank, CA, United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1987
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
H-1361
NASA-CR-166623
NAS 1.26:166623
Accession Number
87N22685
Funding Number(s)
PROJECT: RTOP 505-43-81
CONTRACT_GRANT: NASA ORDER E-69204
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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