Accession Number : AD0664520

Title :   SH-3A TAIL ROTOR-PYLON WIND TUNNEL STUDY.

Descriptive Note : Final rept.,

Corporate Author : UNITED AIRCRAFT CORP STRATFORD CONN SIKORSKY AIRCRAFT DIV

Personal Author(s) : Szustak,Leonard S.

Report Date : SEP 1966

Pagination or Media Count : 199

Abstract : The report presents the results of a wind tunnel study which was conducted to investigate tail rotor autorotation as a means of sustaining flight in the event of a tail rotor drive system malfunction; and to obtain tail rotor characteristics in sideward flight and high speed flight. The wind tunnel study was conducted on an SH-3A helicopter tail rotor and pylon assembly. Tail rotor autorotative conditions were achieved and a limited analytical application of the data showed that forward flight could be sustained with the tail rotor in autorotation and suggested that entry into tail rotor autorotation may be difficult, requiring close attention and some unnatural control inputs by the pilot. Tests of the tail rotor in left sideward flight revealed no non-linearities or instabilities even though the tail rotor was operating in the vortex ring regime. Tail rotor performance, flapping and stress data were gathered to a maximum high speed of 172 knots. (Author)

Descriptors :   (*HELICOPTERS, TAIL HELICOPTER ROTORS), (*TAIL HELICOPTER ROTORS, PERFORMANCE(ENGINEERING)), ROTATION, WIND TUNNEL MODELS, AIRCRAFT PROTUBERANCES, SUPPORTS, FAILURE, LEVEL FLIGHT, MODEL TESTS, STABILITY, VORTICES, STRESSES, HANDLING

Subject Categories : Helicopters

Distribution Statement : APPROVED FOR PUBLIC RELEASE