NDLI: Evaluation of icing scaling on swept naca 0012 airfoil models

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Evaluation of icing scaling on swept naca 0012 airfoil models

Content Provider	NASA Technical Reports Server (NTRS)
Author	Tsao, Jen-Ching Lee, Sam
Copyright Year	2012
Description	Icing scaling tests in the NASA Glenn Icing Research Tunnel (IRT) were performed on swept wing models using existing recommended scaling methods that were originally developed for straight wing. Some needed modifications on the stagnation-point local collection efficiency (i.e., beta(sub 0) calculation and the corresponding convective heat transfer coefficient for swept NACA 0012 airfoil models have been studied and reported in 2009, and the correlations will be used in the current study. The reference tests used a 91.4-cm chord, 152.4-cm span, adjustable sweep airfoil model of NACA 0012 profile at velocities of 100 and 150 knot and MVD of 44 and 93 mm. Scale-to-reference model size ratio was 1:2.4. All tests were conducted at 0deg angle of attack (AoA) and 45deg sweep angle. Ice shape comparison results were presented for stagnation-point freezing fractions in the range of 0.4 to 1.0. Preliminary results showed that good scaling was achieved for the conditions test by using the modified scaling methods developed for swept wing icing.
File Size	1405423
Page Count	22
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20120009186
Archival Resource Key	ark:/13960/t20c9z50c
Language	English
Publisher Date	2012-05-01
Access Restriction	Open
Subject Keyword	Air Transportation And Safety Sweep Angle Convective Heat Transfer Correlation Swept Wings Scale Models Aircraft Icing Stagnation Point Shapes Angle of Attack Heat Transfer Coefficients Ice Formation Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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