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AERODYNAMIC DEVELOPMENT OF THE OH-6A HELICOPTER FOR THE ARMY
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English
Abstract
The aerodynamic development program of the OH-6A Light Observation Helicopter to meet the key Army performance requirements of hover ceiling at 95°F ambient temperature, maximum speed, and cruise endurance is discussed. Also discussed are the stability and control characteristics that have been produced by use of an offset flapping hinge articulated rotor and without resorting to the complications and weight penalties of control system boost or stability augmentation systems. These performance, stability, and control characteristics have been achieved while meeting the Army's primary requirements of small size, light weight, and simplicity.
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Authors
Citation
Amer, K., "AERODYNAMIC DEVELOPMENT OF THE OH-6A HELICOPTER FOR THE ARMY," SAE Technical Paper 640347, 1964, https://doi.org/10.4271/640347.Also In
References
- Harned, Malcolm Development of the OH-6A or Maximum Performance and Efficiency presented at the Twentieth Annual National Forum of the American Helicopter Society May 13-14-15 1964
- Perkins, Courtland D. Hage, Robert E. Airplane Performance Stability and Control John Wiley & Sons, Inc. New York, N. Y March 1950
- Amer, Kenneth B. Means for Achieving Desirable Handling Characteristics in a Small Helicopter Proceedings of the Fifteenth Annual National Forum, American Helicopter Society May 7-8-9 1959