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High Reynolds number tests of the CAST 10-2/DOA 2 airfoil in the Langley 0.3-meter transonic cryogenic tunnel, phase 1A wind tunnel investigation of an advanced technology airfoil, the CAST 10-2/DOA 2, was conducted in the Langley 0.3 meter Transonic Cryogenic Tunnel (0.3 m TCT). This was the first of a series of tests conducted in a cooperative National Aeronautics and Space Administration (NASA) and the Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt e. V. (DFVLR) airfoil research program. Test temperature was varied from 280 K to 100 K to pressures from slightly above 1 to 5.8 atmospheres. Mach number was varied from 0.60 to 0.80, and the Reynolds number (based on airfoil chord) was varied from 4 x 10 to the 8th power to 45 x 10 to the 6th power. This report presents the experimental aerodynamic data obtained for the airfoil and includes descriptions of the airfoil model, the 0.3 m TCT, the test instrumentation, and the testing procedures.
Document ID
19830017389
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Dress, D. A. (Kentron International, Inc. Hampton, VA, United States)
Mcguire, P. D. (NASA Langley Research Center Hampton, VA, United States)
Stanewsky, E. (DFVLR)
Ray, E. J. (NASA Langley Research Center)
Date Acquired
September 4, 2013
Publication Date
May 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-84620
NAS 1.15:84620
Accession Number
83N25660
Funding Number(s)
PROJECT: RTOP 505-31-53-10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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