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- W1986658719 abstract "This paper summarizes the results of the NH-3A high-speed compound helicopter rotor loads flight-test program supported by NASC and USAAVLABS. The aircraft was instrumented to measure: blade aerodynamic pressures on the main rotor blade; blade response in the flatwise, edgewise, and torsion directions; hub forces using a blade root response measurement method; and airframe response. Rotor advance ratio, lift, and propulsion were varied to determine their effects on rotor loads and vibration. Data were acquired at airspeeds as high as 185 knots to provide data required for high-speed compound design. Results are shown of a correlation study comparing test data with analytic data obtained from a Sikorsky blade dynamic analysis, coupled with a variable inflow program originally developed by Cornell Aeronautical Laboratory and modified by United Aircraft Corporation Research Laboratories (UACRL). Hub forces were successfully measured using the blade root response method. Vibratory in-plane rotor hub forces are much higher than the vertical forces and increase with increase in airspeed, whereas the vertical forces are insensitive to airspeed. Increasing rotor lift or advance ratio increases vibratory hub forces and blade bending moments, whereas a lesser effect is seen due to variation in rotor propulsion." @default.
- W1986658719 created "2016-06-24" @default.
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- W1986658719 date "1969-09-01" @default.
- W1986658719 modified "2023-09-24" @default.
- W1986658719 title "Airload, blade response, and hub force measurements on the NH-3A compound helicopter." @default.
- W1986658719 cites W256140563 @default.
- W1986658719 doi "https://doi.org/10.2514/3.44075" @default.
- W1986658719 hasPublicationYear "1969" @default.
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