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. (Author)
Aerodynamic Tests of an Operational OH-6A Helicopter in the Ames 40 Ft X 80 Ft Wind Tunnel
1970
148 pages
Report
Keine Angabe
Englisch
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