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Comparison of airfoil results from an adaptive wall test section and a porous wall test sectionTwo wind tunnel investigations were conducted to assess two different wall interference alleviation/correction techniques: adaptive test section walls and classical analytical corrections. The same airfoil model has been tested in the adaptive wall test section of the NASA-Langley 0.3 m Transonic Cryogenic Tunnel (TCT) and in the National Aeronautical Establishment (NAE) High Reynolds Number 2-D facility. The model has a 9 in. chord and a CAST 10-2/DOA 2 airfoil section. The 0.3 m TCT adaptive wall test section has four solid walls with flexible top and bottom walls. The NAE test section has porous top and bottom walls and solid side walls. The aerodynamic results corrected for top and bottom wall interference at Mach numbers from 0.3 to 0.8 at a Reynolds number of 10 by 1,000,000. Movement of the adaptive walls was used to alleviate the top and bottom wall interference in the test results from the NASA tunnel.
Document ID
19890011589
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mineck, Raymond E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1989
Publication Information
Publication: Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2
Subject Category
Aerodynamics
Accession Number
89N20960
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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