Path: AC/Aircraft
% DC 8 stability derivatives model. -------------------------------------------------------------------------- Form: x = DC8( q, n ) -------------------------------------------------------------------------- ------ Inputs ------ q String describing the type of data n Set ------- Outputs ------- x The properties -------------------------------------------------------------------------- Reference: McRuer, D., Ashenas, I., and D. Graham, Aircraft Dynamics and Automatic Control, Princeton, 1973, pp. 711-714 --------------------------------------------------------------------------
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