Aerodynamic Tests of an Operational OH-6A Helicopter in the Ames 40 FT X 80 Ft Wind Tunnel
Final rept. Jun 1966-May 1970
HUGHES TOOL CO CULVER CITY CA AIRCRAFTDIV
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The report presents a comparative evaluation of the aerodynamic characteristics of an operational OH-6A helicopter as obtained from wind tunnel tests performed in the NASA-Ames 40X80 foot wind tunnel, flight tests, and digital computer studies. The objectives were Explore helicopter and rotor component stability derivatives and performance Simulate use of increased solidity by conducting a portion of the wind tunnel tests at values of thrust corresponding to approximately one-half flight values Conduct analytical studies involving use of digital computing techniques Measurement of rotor blade and rotor mast moments.