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Investigation of sidewall boundary layer removal effects on two different chord airfoil models in the Langley 0.3-meter Transonic Cryogenic TunnelAn investigation was carried out on two CAST 10-2 airfoil models with chords of 3 in. and 6 in. To evaluate the extent of sidewall influence on airfoil tests at transonic Mach numbers. The tests were conducted in the Langley 0.3-m Transonic Cryogenic Tunnel two-dimensional test section equipped with an upstream sidewall boundary layer removal system which reduces the boundary layer displacement thickness to about 1 percent of model halfspan from an initial 2 percent without boundary layer removal. Test results have shown the changes in the location of the shock on the upper surface of the airfoil to be about the same for both models with and without sidewall boundary layer removal. Even though large differences were noted in the high lift characteristics of the two models, the sidewall boundary layer removal had little effect on the differences. These tests also served to validate the boundary layer removal technique and the associated Mach number correction required with upstream boundary layer removal.
Document ID
19840041400
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Murthy, A. V.
(Old Dominion University Norfolk, VA, United States)
Johnson, C. B.
(Old Dominion Coll. Norfolk, VA, United States)
Ray, E. J.
(NASA Langley Research Center Transonic Aerodynamics Div., Hampton, VA, United States)
Stanewsky, E.
(Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt Goettingen, Germany)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 84-0598
Accession Number
84A24187
Distribution Limits
Public
Copyright
Other

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