Abstract
The procedure for calculation of critical flutter speeds of an aircraft in subsonic flow on minicomputer, is displayed in the paper. Problem of vibrational assymmetry, determined during vibrational tests, is solved using decomposition of each mode into inertialy normalised symmetrical and antisyrnmetrical parts. Unsteady aerodynamic loadings are determined by the doublet-lattice method. Modest memory of minicomputer used dictated the choice of the method of optimal elimination for solution of an assymmetric system of complex linear equations. Interpolation of total matrices of generalised aerodynamical forces is done by, in this paper proposed, modified method of natural cubic spline. Flutter eigenvalues are calculated using iterative Laguerre's procedure.
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