A method is presented for obtaining Influence coefficients for thin low-aspect-ratio wings of built-up construction. Chordwise deflections arc assailed to le parabolic (or linear) and the principle of minimum potential energy is used in conjunction with difference equivalents to option an appropriate set of equilibrium equations. Symmetric and antisymetric loud-support conditions are considered. A simple method is riving Tor taking account of attachment to a flexible fuselage. The com¬putations involved are for the most part, organized into matrix form so as to be suitable for high-speed computing machines. The matrices needed at the beginning of the; computing process can be set up directly from the data of the wing design.
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