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F-8 oblique wing structural feasibility studyThe feasibility of fitting a rotating oblique wing on an F-8 aircraft to produce a full scale manned prototype capable of operating in the transonic and supersonic speed range was investigated. The strength, aeroelasticity, and fatigue life of such a prototype are analyzed. Concepts are developed for a new wing, a pivot, a skewing mechanism, control systems that operate through the pivot, and a wing support assembly that attaches in the F-8 wing cavity. The modification of the two-place NTF-8A aircraft to the oblique wing configuration is discussed.
Document ID
19770023163
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Koltko, E. (LTV Aerospace Corp. Dallas, TX, United States)
Katz, A. (LTV Aerospace Corp. Dallas, TX, United States)
Bell, M. A. (LTV Aerospace Corp. Dallas, TX, United States)
Smith, W. D. (LTV Aerospace Corp. Dallas, TX, United States)
Lauridia, R. (LTV Aerospace Corp. Dallas, TX, United States)
Overstreet, C. T. (LTV Aerospace Corp. Dallas, TX, United States)
Klapprott, C. (LTV Aerospace Corp. Dallas, TX, United States)
Orr, T. F. (LTV Aerospace Corp. Dallas, TX, United States)
Jobe, C. L. (LTV Aerospace Corp. Dallas, TX, United States)
Wyatt, F. G. (LTV Aerospace Corp. Dallas, TX, United States)
Date Acquired
September 3, 2013
Publication Date
November 1, 1975
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
REPT-2-57000/5R-3239
NASA-CR-154841
Report Number: REPT-2-57000/5R-3239
Report Number: NASA-CR-154841
Accession Number
77N30107
Funding Number(s)
CONTRACT_GRANT: NAS4-2266
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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