Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10

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

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Description

Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and 3 x 10 based on nominal leading-edge diameter. The model simulated the bottom of a 75 deg delta wing at 8O deg angle of attack. The data indicated that for the test conditions a modified three-dimensional stagnation-point theory will predict to reasonable engineering accuracy the heating on a highly swept wing leading edge, the heating being reduced by sweep by the 3/2 power of the cosine ... continued below

Creation Information

Swanson, A. G. September 10, 1958.

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

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  • Main Title: Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10
  • Series Title: NACA Research Memorandums

Description

Heat-transfer measurements were made on a simulated glide-rocket
shape in free flight at Mach numbers up to 10 and free-stream Reynolds
numbers of 2 x 10 based on distance along surface from apex and 3 x 10
based on nominal leading-edge diameter. The model simulated the bottom
of a 75 deg delta wing at 8O deg angle of attack. The data indicated that for
the test conditions a modified three-dimensional stagnation-point theory
will predict to reasonable engineering accuracy the heating on a highly
swept wing leading edge, the heating being reduced by sweep by the
3/2 power of the cosine of the sweep angle. The data also indicate that
laminar heating rates over the windward surface of a highly swept flat
glider wing at moderate angles of attack can be predicted with reasonable
engineering accuracy by flat-plate theory using wedge local flow conditions
and basing Reynolds numbers on lengths from the wing leading edge
parallel to the surface center line.

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  • : 63N20530
  • URL: http://hdl.handle.net/2060/19630010650 External Link
  • Report No.: NACA-RM-L58G03
  • Center for AeroSpace Information Number: 19630010650
  • Archival Resource Key: ark:/67531/metadc52943

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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

  • September 10, 1958

Added to The UNT Digital Library

  • Nov. 11, 2011, 7:22 p.m.

Description Last Updated

  • Jan. 27, 2017, 2:27 p.m.

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Citations, Rights, Re-Use

Swanson, A. G. Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10, report, September 10, 1958; (digital.library.unt.edu/ark:/67531/metadc52943/: accessed September 19, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.