Flight Characteristics Test of the UH-60A with Tail Boom Mounted Strake
Final rept. 11-19 Aug 1986
ARMY AVIATION SYSTEMS COMMAND ST LOUIS MO
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Testing was conducted to evaluate the effect of a tail-boom mounted strake on the performance and handling qualities of the UH-60A helicopter. A total of 2.0 productive flight hours were flown between 11-19 Aug 1986. The UH- 60A helicopters overall performance in hover and sideward flight to 45 knots true airspeed KTAS is essentially unchanged by the strake installation. There was on overall effect of the strake installation on the UH-60As flight control margins, except for a slight reduction in right cyclic control displacement increase in control margin required in right sideward flight. There was a minor improvement in longitudinal cyclic pilot workload in left and right sideward flight to 15 KTAS. The pilot did not detect a significant difference in flying qualities with the strake installed. This test reflected little change with the strake installed. Previous US Army Aviation Engineering Flight Activity performance and flying qualities evaluations of the UH-60A without a tail boom mounted strake have found no control margin or power required problems with sideward flight. Consequently, no further strake testing should be conducted on the UH-60A helicopter. The UH-1H helicopter, which has a documented problem with tail rotor control margins during hover and sideward flight, should be considered a candidate for a tail boom strake evaluation.