Evaluation of Icing Scaling on Swept NACA 0012 Airfoil Models

2011-38-0081

06/13/2011

Event
SAE 2011 International Conference on Aircraft and Engine Icing and Ground Deicing
Authors Abstract
Content
Icing scaling tests in the NASA Glenn Icing Research Tunnel 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., Β₀) 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 knots and MVD of 44 and 93 μm. Scale-to-reference model size ratio was 1:2.4. All tests were conducted at 0° angle of attach (AoA) and 45° 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.
Meta TagsDetails
DOI
https://doi.org/10.4271/2011-38-0081
Pages
12
Citation
Tsao, J., and Lee, S., "Evaluation of Icing Scaling on Swept NACA 0012 Airfoil Models," SAE Technical Paper 2011-38-0081, 2011, https://doi.org/10.4271/2011-38-0081.
Additional Details
Publisher
Published
Jun 13, 2011
Product Code
2011-38-0081
Content Type
Technical Paper
Language
English