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Investigation of Materials for Boundary Layer Control in a Supersonic Wind Tunnel
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Author and Affiliation:
Braafladt, Alexander(Minnesota Univ., Undergraduate Student Research Program, Minneapolis, MN, United States);
Lucero, John M.(NASA Glenn Research Center, Cleveland, OH, United States);
Hirt, Stefanie M.(NASA Glenn Research Center, Cleveland, OH, United States)
Abstract: During operation of the NASA Glenn Research Center 15- by 15-Centimeter Supersonic Wind Tunnel (SWT), a significant, undesirable corner flow separation is created by the three-dimensional interaction of the wall and floor boundary layers in the tunnel corners following an oblique-shock/ boundary-layer interaction. A method to minimize this effect was conceived by connecting the wall and floor boundary layers with a radius of curvature in the corners. The results and observations of a trade study to determine the effectiveness of candidate materials for creating the radius of curvature in the SWT are presented. The experiments in the study focus on the formation of corner fillets of four different radii of curvature, 6.35 mm (0.25 in.), 9.525 mm (0.375 in.), 12.7 mm (0.5 in.), and 15.875 mm (0.625 in.), based on the observed boundary layer thickness of 11.43 mm (0.45 in.). Tests were performed on ten candidate materials to determine shrinkage, surface roughness, cure time, ease of application and removal, adhesion, eccentricity, formability, and repeatability. Of the ten materials, the four materials which exhibited characteristics most promising for effective use were the heavy body and regular type dental impression materials, the basic sculpting epoxy, and the polyurethane sealant. Of these, the particular material which was most effective, the heavy body dental impression material, was tested in the SWT in Mach 2 flow, and was observed to satisfy all requirements for use in creating the corner fillets in the upcoming experiments on shock-wave/boundary-layer interaction.
Publication Date: Nov 01, 2013
Document ID:
20140003935
(Acquired May 08, 2014)
Subject Category: AERODYNAMICS
Report/Patent Number: NASA/TM-2013-217894, E-18708
Document Type: Technical Report
Meeting Information: Machinery Failure Prevention Technology (MFPT) 2013; 13-17 May, 2013; Cleveland, OH; United States
International Instrumentaiton Symposium (IIS); 59th; 13-17 May, 2013; Cleveland, OH; United States
Financial Sponsor: NASA Glenn Research Center; Cleveland, OH, United States
Description: 24p; In English; Original contains color illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution as joint owner in the copyright
NASA Terms: SUPERSONIC WIND TUNNELS; WIND TUNNEL TESTS; BOUNDARY LAYERS; BOUNDARY LAYER SEPARATION; SHOCK WAVE INTERACTION; MATERIALS TESTS; BOUNDARY LAYER CONTROL; CORNERS; FILLETS; SURFACE ROUGHNESS; ECCENTRICITY; REYNOLDS NUMBER
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