Results of wind tunnel testing of a multicyclic controllable twist rotor at several flight conditions and advance ratios of 0.22 and 0.33 are evaluated. It is found that blade flatwise bending moments and root control actuator loads (fixed system) can be reduced with multicyclic control. Flatwise bending moment reductions of 22-30% with concurrent 83% reductions in control loads were predicted. Analysis of profile power changes indicates a decrease in profile power coefficient of 0.00016, corresponding to a loss of 0.12 sq m of equivalent drag area.
Wind-tunnel test results of a full-scale multicyclic controllable twist rotor
In: American Helicopter Society, Annual National Forum ; 1978 ; Washington, DC
1978-01-01
Miscellaneous
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English
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