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A wall interference assessment/correction systemA Wall Signature method originally developed by Hackett was selected to be adapted for the Ames 12-ft Wind Tunnel Wall Interference Assessment/Correction (WIAC) System in the project. This method uses limited measurements of the static pressure at the wall, in conjunction with the solid wall boundary condition, to determine the strength and distribution of singularities representing the test article. The singularities are used in turn for estimating wall interference at the model location. The lifting interference will be treated separately by representing in a horseshoe vortex system for the model's lifting effects. The development and implementation of a working prototype will be completed, delivered, and documented with a software manual. The WIAC code will be validated by conducting numerically simulated experiments rather than actual wind tunnel experiments. The simulations will be used to generate both free-air and confined wind-tunnel flow fields for each of the test articles over a range of test configurations. Specifically, the pressure signature at the test section wall will be computed for the tunnel case to provide the simulated 'measured' data. These data will serve as the input for the WIAC method - Wall Signature method. The performance of the WIAC method then may be evaluated by comparing the corrected parameters with those for the free-air simulation. The following two additional tasks are included in the supplement No. 1 to the basic Grant. On-line wall interference calculation: The developed wall signature method (modified Hackett's method) for Ames 12-ft Tunnel will be the pre-computed coefficients which facilitate the on-line calculation of wall interference; and support system effects estimation: The effects on the wall pressure measurements due to the presence of the model support systems will be evaluated.
Document ID
19940008603
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Lo, Ching F.
(Tennessee Univ. Space Inst. Tullahoma, TN, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:194174
NASA-CR-194174
Report Number: NAS 1.26:194174
Report Number: NASA-CR-194174
Accession Number
94N13076
Funding Number(s)
CONTRACT_GRANT: NAG2-733
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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