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The development of a self-streamlining flexible walled transonic test sectionThis design eliminates the uncertainties in data from conventional transonic test sections. Sidewalls are rigid, and the flexible floor and ceiling are positioned by motorized jacks controlled by on-line computer to minimize run times. The tunnel-computer combination is self-streamlining without reference to the model. Data is taken from the model only when the walls are good streamlines, and is corrected for the small, known but inevitable residual interferences. Two-dimensional validation testing in the Mach range up to about 0.85 where the walls are just supercritical shows good agreement with reference data using a height:chord ratio of 1.5. Techniques are under development to extend Mach number above 1. This work has demonstrated the feasibility of almost eliminating wall interferences, improving flow quality, and reducing power requirements or increasing Reynolds number. Extensions to three-dimensional testing are outlined.
Document ID
19800042794
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Goodyer, M. J.
(Southampton Univ. United Kingdom)
Wolf, S. W. D.
(Southampton University Southampton, United Kingdom)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 80-0440
Meeting Information
Meeting: Aerodynamic Testing Conference
Location: Colorado Springs, CO
Start Date: March 18, 1980
End Date: March 20, 1980
Accession Number
80A26964
Funding Number(s)
CONTRACT_GRANT: NSG-7172
Distribution Limits
Public
Copyright
Other

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