Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 24

One of 4,120 reports in the series: NACA Technical Notes available on this site.

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Description

This note is the fifth of a series covering an investigation of a number of related airfoils. It presents the results obtained from tests of a group of six low-cambered airfoils in the variable-density wind tunnel. The mean camber lines are identical for the six airfoils and are of such a form that the maximum mean camber is 2 per cent of the chord and is at a position 0.4 of the chord behind the loading edge. The airfoils differ in thickness only, the maximum-thickness/chord ratios being 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21. The results have been presented in ... continued below

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Jacobs, Eastman N. & Ward, Kenneth E. January 1, 1932.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and one other and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 3375 times , with 27 in the last month . More information about this report can be viewed below.

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  • Main Title: Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 24
  • Series Title: NACA Technical Notes

Description

This note is the fifth of a series covering an investigation of a number of related airfoils. It presents the results obtained from tests of a group of six low-cambered airfoils in the variable-density wind tunnel. The mean camber lines are identical for the six airfoils and are of such a form that the maximum mean camber is 2 per cent of the chord and is at a position 0.4 of the chord behind the loading edge. The airfoils differ in thickness only, the maximum-thickness/chord ratios being 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21. The results have been presented in the form of both infinite and finite aspect-ratio characteristics. The values of C(sub L) max/C(sub d) degrees min for this group of airfoils are among the highest thus far obtained, the minimum profile drags being approximately equal to those for the symmetrical series of corresponding thickness, while the maximum lift coefficients are considerably higher.

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  • : 93R10444
  • URL: http://hdl.handle.net/2060/19930081154 External Link
  • Report No.: NACA-TN-404
  • Center for AeroSpace Information Number: 19930081154
  • Archival Resource Key: ark:/67531/metadc54043

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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).

Technical Report Archive and Image Library

This selection of materials from the Technical Report Archive and Image Library (TRAIL) includes hard-to-find reports published by various government agencies. The technical publications contain reports, images, and technical descriptions of research performed for U.S. government agencies. Topics range from mining, desalination, and radiation to broader physics, biology, and chemistry studies. Some reports include maps, foldouts, blueprints, and other oversize materials.

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Creation Date

  • January 1, 1932

Added to The UNT Digital Library

  • Nov. 14, 2011, 7:18 p.m.

Description Last Updated

  • Feb. 6, 2017, 7:26 p.m.

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Jacobs, Eastman N. & Ward, Kenneth E. Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 24, report, January 1, 1932; (digital.library.unt.edu/ark:/67531/metadc54043/: accessed October 23, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.