Experimental Droplet Impingement on Several Two-Dimensional Airfoils with Thickness Ratios of 6 to 16 Percent

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Description

The rate and area of cloud droplet impingement on several two-dimensional swept and unswept airfoils were obtained experimentally in the NACA Lewis icing tunnel with a dye-tracer technique. Airfoil thickness ratios of 6 to 16 percent; angles of attack from 0 deg to 12 deg, and chord sizes from 13 to 96 inches were included in the study. The data were obtained at 152 knots and are extended to other conditions by dimensionless impingement parameters. In general, the data show that the total and local collection efficiencies and impingement limits are primary functions of the modified inertia parameter (in which ... continued below

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Gelder, Thomas F.; Smyers, William H., Jr. & VonGlahn, Uwe December 1, 1956.

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  • Main Title: Experimental Droplet Impingement on Several Two-Dimensional Airfoils with Thickness Ratios of 6 to 16 Percent
  • Series Title: NACA Technical Notes

Description

The rate and area of cloud droplet impingement on several two-dimensional
swept and unswept airfoils were obtained experimentally in
the NACA Lewis icing tunnel with a dye-tracer technique. Airfoil thickness
ratios of 6 to 16 percent; angles of attack from 0 deg to 12 deg, and
chord sizes from 13 to 96 inches were included in the study. The data
were obtained at 152 knots and are extended to other conditions by dimensionless
impingement parameters.
In general, the data show that the total and local collection efficiencies
and impingement limits are primary functions of the modified
inertia parameter (in which airspeed, droplet size, and body size are
the most significant variables) and the airfoil thickness ratio. Local
collection efficiencies and impingement limits also depend on angle of
attack. Secondary factors affecting impingement characteristics are airfoil
shape, camber, and sweep angle. The impingement characteristics obtained
experimentally for the airfoils were within +/-10 percent on the
average of the characteristics calculated from theoretical trajectories.
Over the range of conditions studied, the experimental data demonstrate
that a specific method can be used to predict the impingement characteristics
of swept airfoils with large aspect ratios from the data for unswept
airfoils of the same series.

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  • Accession or Local Control No: 81N73122
  • URL: http://hdl.handle.net/2060/19810068700 External Link
  • Report No.: NACA-TN-3839
  • Center for AeroSpace Information Number: 19810068700
  • Archival Resource Key: ark:/67531/metadc53503

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National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

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Creation Date

  • December 1, 1956

Added to The UNT Digital Library

  • Nov. 11, 2011, 7:22 p.m.

Description Last Updated

  • April 11, 2018, 3:36 p.m.

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Gelder, Thomas F.; Smyers, William H., Jr. & VonGlahn, Uwe. Experimental Droplet Impingement on Several Two-Dimensional Airfoils with Thickness Ratios of 6 to 16 Percent, report, December 1, 1956; (digital.library.unt.edu/ark:/67531/metadc53503/: accessed September 23, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.