Performance results from a test of an S-76 rotor in the NASA Ames 80- by 120-foot wind tunnelA full-scale helicopter rotor wind tunnel test has been conducted which covers a wide range of rotor-shaft angles-of-attack and 0-100 kt thrust conditions. The hover performance data thus obtained were compared with the results of momentum theory calculations; forward flight rotor-performance data were compared with calculations from a comprehensive rotorcraft analysis. These comparisons suggest that hover testing at an outdoor facility in the absence of ground effect is required to make a final determination of the absolute accuracy of the wind tunnel hover data.
Document ID
19930063214
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Shinoda, Patrick M. (U.S. Army, Aeroflightdynamics Directorate; NASA, Ames Research Center Moffett Field, CA, United States)
Johnson, Wayne (Johnson Aeronautics Palo Alto, CA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA Applied Aerodynamics Conference, 11th, Monterey, CA, Aug. 9-11, 1993, Technical Papers. Pt. 1 (A93-47201 19-02)
Publisher: American Institute of Aeronautics and Astronautics