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Status and capabilities of the National Full Scale Facility 40- by 80-foot wind tunnel modificationThe background, requirements, and aerodynamic design of the modified NASA Ames 40 x 80 ft wind tunnel are reviewed, along with the systems integration and systems test results. Advancing vehicle sizes and airspeeds required a larger wind tunnel test section and a capability for 100 and 300 knots airspeed simulation. Acoustic mufflers at the inlet and exit of the nonreturn circuit provide noise suppression. The enlarged test section is intended to accomodate the complex flowfields of wings with high lift coefficients, and the drive system is designed with minimum residual swirl. Features of the fan blades are examined, along with characteristics of the test channels, control vanes and louvers, the exit, circuit losses, temperature rises during operation of the nonreturn circuit, and the facility acoustics. Specific construction problems and solutions for the conversion process are outlined, and it is noted that operational status is expected at the end of 1982.
Document ID
19820041141
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Mort, K. W.
(NASA Ames Research Center Moffett Field, CA, United States)
Engelbert, D. F.
(NASA Ames Research Center Moffett Field, CA, United States)
Dusterberry, J. C.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 82-0607
Meeting Information
Meeting: In: Aerodynamic Testing Conference
Location: Williamsburg, VA
Start Date: March 22, 1982
End Date: March 24, 1982
Accession Number
82A24676
Distribution Limits
Public
Copyright
Other

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