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The shock tube as a device for testing transonic airfoils at high Reynolds numbersA performance analysis of gas-driven shock tubes shows that transonic airfoil flows with chord Reynolds numbers in the range of 100 million can be generated behind the primary shock in a large shock tube. A study of flow over simple airfoils has been carried out at low and intermediate Reynolds numbers to assess the testing technique. Results obtained from schlieren photos and airfoil pressure measurements show that steady transonic flows similar to those observed for the airfoils in wind tunnels can be generated within the available testing time in a shock tube with either properly-contoured test section walls or a properly-designed slotted-wall test section. The study indicates that the shock tube is a useful facility for studying two-dimensional high Reynolds number transonic airfoil flows.
Document ID
19780048421
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Cook, W. J.
(Iowa State University of Science and Technology, Ames, Iowa, United States)
Presley, L. L.
(Iowa State Univ. of Science and Technology Ames, IA, United States)
Chapman, G. T.
(NASA Ames Research Center Aerodynamics Research Branch, Moffett Field, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1978
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 78-769
Meeting Information
Meeting: Aerodynamic Testing Conference
Location: San Diego, CA
Start Date: April 19, 1978
End Date: April 21, 1978
Accession Number
78A32330
Funding Number(s)
CONTRACT_GRANT: NSG-2152
Distribution Limits
Public
Copyright
Other

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