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Experimental results on a wall interference correction method with interface measurementsA wall interference assessment and correction method for subsonic two-dimensional wind tunnel testing is presented. This method calculates a pressure coefficient and angle of attack correction based on velocity measurements on interfaces inside of the wind tunnel. A mathematical representation of the test article is not required. An experimental verification of the suggested technique is given. A NACA 0012 airfoil is tested at a Mach number of 0.70 and at two different angles of attack. Calculated blockage corrections show reasonable agreement with results based on Hackett's method. Corrected surface pressures compare favorably to free-air flow field data if the tunnel flow field is subsonic. The present wall interference correction method can be applied to transonic tunnel flow fields with some restrictions. Errors are estimated and it is shown that the expected error in calculating the pressure coefficient correction on the model surface is in the order of the error of pressure coefficient measurement on interfaces. Necessary testing equipment in existing tunnels can easily be modified if the present method is applied.
Document ID
19920044354
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lo, C. F.
(NASA Ames Research Center Moffett Field, CA, United States)
Ulbrich, N.
(Tennessee, University Tullahoma, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-0570
Accession Number
92A26978
Funding Number(s)
CONTRACT_GRANT: NAG2-733
Distribution Limits
Public
Copyright
Other

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