Effects of Compressibility on the Flow Past Thick Airfoil Sections

One of 5,164 reports in the series: NACA Research Memorandums available on this site.

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Description

"Six, 3-inch-chord symmetrical airfoil sections having systematic variations in thickness and thickness location were tested at Mach numbers near flight values for propeller-shank sections. The tests, the results of which are presented in the form of schlieren photographs of the flow past each model and pressure-distribution charts for two of the model, were performed to illustrate the effects of compressibility on the flow past thick symmetrical airfoil sections. Representative flow photographs indicated that at Mach numbers approximately 0.05 above the critical Mach number a speed region was reached in which the flow oscillated rapidly and the separation point and the ... continued below

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[33] p. : ill.

Creation Information

Daley, Bernard N. & Humphreys, Milton D. January 30, 1947.

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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 53 times . More information about this report can be viewed below.

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Description

"Six, 3-inch-chord symmetrical airfoil sections having systematic variations in thickness and thickness location were tested at Mach numbers near flight values for propeller-shank sections. The tests, the results of which are presented in the form of schlieren photographs of the flow past each model and pressure-distribution charts for two of the model, were performed to illustrate the effects of compressibility on the flow past thick symmetrical airfoil sections. Representative flow photographs indicated that at Mach numbers approximately 0.05 above the critical Mach number a speed region was reached in which the flow oscillated rapidly and the separation point and the location of the shock wave were unstable" (p. 1).

Physical Description

[33] p. : ill.

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  • URL: http://hdl.handle.net/2060/20050071700 External Link
  • Report No.: NACA-RM-L6J17a
  • Center for AeroSpace Information Number: 20050071700
  • Archival Resource Key: ark:/67531/metadc64883

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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

  • January 30, 1947

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

Description Last Updated

  • July 10, 2018, 4:25 p.m.

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Daley, Bernard N. & Humphreys, Milton D. Effects of Compressibility on the Flow Past Thick Airfoil Sections, report, January 30, 1947; (digital.library.unt.edu/ark:/67531/metadc64883/: accessed October 16, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.