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Experimental Investigation of Water Droplet Impingement on Airfoils, Finite Wings, and an S-duct Engine InletValidation of trajectory computer codes, for icing analysis, requires experimental water droplet impingement data for a wide range of aircraft geometries as well as flow and icing conditions. This report presents improved experimental and data reduction methods for obtaining water droplet impingement data and provides a comprehensive water droplet impingement database for a range of test geometries including an MS(1)-0317 airfoil, a GLC-305 airfoil, an NACA 65(sub 2)-415 airfoil, a commercial transport tail section, a 36-inch chord natural laminar flow NLF(1)-0414 airfoil, a 48-inch NLF(1)-0414 section with a 25 percent chord simple flap, a state-of-the-art three-element high lift system, a NACA 64A008 finite span swept business jet tail, a full-scale business jet horizontal tail section, a 25 percent-scale business jet empennage, and an S-duct turboprop engine inlet. The experimental results were obtained at the NASA Glenn Icing Research Tunnel (IRT) for spray clouds with median volumetric diameter (MVD) of 11, 11.5, 21, 92, and 94 microns and for a range of angles of attack. The majority of the impingement experiments were conducted at an air speed of 175 mph corresponding to a Reynolds number of approximately 1.6 million per foot. The maximum difference of repeated tests from the average ranged from 0.24 to 12 percent for most of the experimental results presented. This represents a significant improvement in test repeatability compared to previous experimental studies. The increase in test repeatability was attributed to improvements made to the experimental and data reduction methods. Computations performed with the LEWICE-2D and LEWICE-3D computer codes for all test configurations are presented in this report. For the test cases involving median volumetric diameters of 11 and 21 microns, the correlation between the analytical and experimental impingement efficiency distributions was good. For the median volumetric diameters of 92 and 94-micron cases, however, the analysis produced higher impingement efficiencies and larger impingement limits than the experiment. It is speculated that this discrepancy is due to droplet splashing and breakup experienced by large droplets during impingement.
Document ID
20020090796
Document Type
Technical Memorandum (TM)
Authors
Papadakis, Michael (Wichita State Univ. Wichita, KS United States)
Hung, Kuohsing E. (Wichita State Univ. Wichita, KS United States)
Vu, Giao T. (Boeing Co. Wichita, KS United States)
Yeong, Hsiung Wei (Wichita State Univ. Wichita, KS United States)
Bidwell, Colin S. (NASA Glenn Research Center Cleveland, OH United States)
Breer, Martin D. (Boeing Co. Wichita, KS United States)
Bencic, Timothy J. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
October 1, 2002
Subject Category
Air Transportation and Safety
Report/Patent Number
NAS 1.15:211700
NASA/TM-2002-211700
E-13444
Funding Number(s)
CONTRACT_GRANT: NAG3-1985
PROJECT: RTOP 708-20-13
CONTRACT_GRANT: NAG3-1775
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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