4-ft diam 2-blade rotor was tested in 300-mph 7×10 ft Langley tunnel to study effect of blade collective pitch angle, rotor angle of attack, flapping hinge offset, and tip speed ratio during stages of transformation between helicopter and autogiro configuration; results obtained.
Wind-tunnel investigation of effect of angle of attack and flapping-hinge offset on periodic bending moments and flapping of small rotor
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo n 3-3-59L
1959
44 pages
Report
Englisch
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