Several state‐of‐the‐art methods for predicting helicopter rotor loads were used by ten contributors to calculate rotor blade loads including airloads, bending moments, vibratory hub shears, and other parameters for a hypothetical helicopter rotor. Three different
advance ratios were treated: μ = 0.1, 0.2, and 0.33. Comparisons of results obtained by the various contributors indicate significant differences for certain parameters and flight conditions.
Trim parameters and flapwise bending moments show the smallest variations, while chordwise bending moments, torsional moments, and vibratory shears show moderate to large differences. Torsional moment variations were most sensitive to advance ratio. Analysis of the results indicates that the
differences can be attributed to all three fundamental parts of the problem: numerical solution methods, structural dynamics, and aerodynamics.
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Document Type: Research Article
Ames Directorate, U.S. Army Air Mobility R&D Laboratory, Moffett Field, California 94035
Publication date: 1974-10-01
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