Abstract
Abstract : The purpose of this program was to study the aerodynamic and aeroelastic behavior of a rigid two-bladed rotor system operating at steady- state advance ratios up to approximately 15. Also to be investigated was the operation of this rotor during periods of acceleration and deceleration which were representative of the starting/stopping sequence of a stowable rotor. The objective of the program was accomplished by conducting wind tunnel tests in the NASA-Ames 40- x 80-foot wind tunnel on a full-scale rotor. Hub forces and moments, blade pressure distributions (chordwise and spanwise), and blade flatwise, chordwise and torsional moments were measured. The experimental results were used to correlate with existing theory.
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