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Applications at M = 1 of a method for solving the subsonic problem of the oscillating finite wing with the aid of high-speed digital computers

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Abstract

An aeroplane may be most susceptible to flutter in the transonic part of its speed range. Therefore, it is essential that theoretical flutter investigations can be carried out at Mach numbers in the vicinity of one. And for this purpose one must be able to calculate the aerodynamic forces which arise due to the flutter mode.

The author is indebted to S. Lidin for preparation of computer programs.

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References

  1. Davies, D. E.: Three-dimensional sonic theory. Manual on aeroelasticity. Part II. Aerodynamic aspects. Chap. 4. AGARD, Paris, 1961.

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Author information

Authors and Affiliations

  1. Svenska Aeroplan Aktiebolaget, Linköping, Sverige

    Valter J. E. Stark

Authors
  1. Valter J. E. Stark
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Editor information

Klaus Oswatitsch

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© 1964 Springer-Verlag OHG., Berlin/Göttingen/Heidelberg

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Stark, V.J.E. (1964). Applications at M = 1 of a method for solving the subsonic problem of the oscillating finite wing with the aid of high-speed digital computers. In: Oswatitsch, K. (eds) Symposium Transsonicum. International Union of Theoretical and Applied Mechanics (IUTAM) / Internationale Union für Theoretische und Angewandte Mechanik (IUTAM). Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-88337-8_28

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  • DOI: https://doi.org/10.1007/978-3-642-88337-8_28

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-642-48450-6

  • Online ISBN: 978-3-642-88337-8

  • eBook Packages: Springer Book Archive

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