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
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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
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