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Low-speed wind tunnel test results of the Canard Rotor/Wing conceptThe Canard Rotor/Wing (CRW), a high-speed rotorcraft concept, was tested at the National Aeronautics and Space Administration (NASA) Ames Research Center's 40- by 80-Foot Wind Tunnel in Mountain View, California. The 1/5-scale model was tested to identify certain low-speed, fixed-wing, aerodynamic characteristics of the configuration and investigate the effectiveness of two empennages, an H-Tail and a T-Tail. The paper addresses the principal test objectives and the results achieved in the wind tunnel test. These are summarized as: i) drag build-up and differences between the H-Tail and T-Tail configuration, ii) longitudinal stability of the H-Tail and T-Tail configurations in the conversion and cruise modes, iii) control derivatives for the canard and elevator in the conversion and cruise modes, iv) aerodynamic characteristics of varying the rotor/wing azimuth position, and v) canard and tail lift/trim capability for conversion conditions.
Document ID
19930063212
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bass, Steven M.
(NASA Ames Research Center Moffett Field, CA, United States)
Thompson, Thomas L.
(NASA Ames Research Center Moffett Field, CA, United States)
Rutherford, John W.
(McDonnell Douglas Helicopter Co. Mesa, AZ, United States)
Swanson, Stephen
(Sterling Software, Inc.; NASA, Ames Research Center Moffett Field, 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
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-3412
Accession Number
93A47209
Distribution Limits
Public
Copyright
Other

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