A Report on Stability and Control Testing of a Tilt Wing V/STOL Aircraft 660315

A limited test program is being conducted on a prototype of the Canadair CL-84 tilt-wing V/STOL aircraft to evaluate its stability and control design objectives. The results to date indicate that only very minor modifications were necessary with regard to the flying control criteria previously established through analysis, fixed-base simulator studies, and variable-stability helicopter tests. In general, the qualitative assessment made thus far of the handling qualities of the CL-84 has proven the adequacy of the established criteria for stability and control performance for systems as complex as that of the CL-84.


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