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Computational analysis of semi-span model test techniquesA computational investigation was conducted to support the development of a semi-span model test capability in the NASA LaRC's National Transonic Facility. This capability is required for the testing of high-lift systems at flight Reynolds numbers. A three-dimensional Navier-Stokes solver was used to compute the low-speed flow over both a full-span configuration and a semi-span configuration. The computational results were found to be in good agreement with the experimental data. The computational results indicate that the stand-off height has a strong influence on the flow over a semi-span model. The semi-span model adequately replicates the aerodynamic characteristics of the full-span configuration when a small stand-off height, approximately twice the tunnel empty sidewall boundary layer displacement thickness, is used. Several active sidewall boundary layer control techniques were examined including: upstream blowing, local jet blowing, and sidewall suction. Both upstream tangential blowing, and sidewall suction were found to minimize the separation of the sidewall boundary layer ahead of the semi-span model. The required mass flow rates are found to be practicable for testing in the NTF. For the configuration examined, the active sidewall boundary layer control techniques were found to be necessary only near the maximum lift conditions.
Document ID
19960028091
Acquisition Source
Langley Research Center
Document Type
Thesis/Dissertation
Authors
Milholen, William E., II (North Carolina State Univ. Raleigh,NC United States)
Chokani, Ndaona (North Carolina State Univ. Raleigh,NC United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1996
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:4709
NASA-CR-4709
Accession Number
96N29182
Funding Number(s)
PROJECT: RTOP 505-59-85-01
CONTRACT_GRANT: NCC1-169
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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