Surface pressure measurements for CFD code validation in hypersonic flow

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Description

Extensive surface pressure measurements were obtained on a hypersonic vehicle configuration at Mach 8. All of the experimental results were obtained in the Sandia National Laboratories Mach 8 hypersonic wind tunnel for laminar boundary layer conditions. The basic vehicle configuration is a spherically blunted 10{degrees} half-angle cone with a slice parallel with the axis of the vehicle. The bluntness ratio of the geometry is 10% and the slice begins at 70% of the length of the vehicle. Surface pressure measurements were obtained for angles of attack from {minus}10 to + 18{degrees}, for various roll angles, at 96 locations on the ... continued below

Physical Description

49 p.

Creation Information

Oberkampf, W.L.; Aeschliman, D.P.; Henfling, J.F. & Larson, D.E. July 1, 1995.

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This report is part of the collection entitled: Office of Scientific & Technical Information Technical Reports and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 23 times , with 6 in the last month . More information about this report can be viewed below.

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  • Sandia National Laboratories
    Publisher Info: Sandia National Labs., Albuquerque, NM (United States)
    Place of Publication: Albuquerque, New Mexico

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Description

Extensive surface pressure measurements were obtained on a hypersonic vehicle configuration at Mach 8. All of the experimental results were obtained in the Sandia National Laboratories Mach 8 hypersonic wind tunnel for laminar boundary layer conditions. The basic vehicle configuration is a spherically blunted 10{degrees} half-angle cone with a slice parallel with the axis of the vehicle. The bluntness ratio of the geometry is 10% and the slice begins at 70% of the length of the vehicle. Surface pressure measurements were obtained for angles of attack from {minus}10 to + 18{degrees}, for various roll angles, at 96 locations on the body surface. A new and innovative uncertainty analysis was devised to estimate the contributors to surface pressure measurement uncertainty. Quantitative estimates were computed for the uncertainty contributions due to the complete instrumentation system, nonuniformity of flow in the test section of the wind tunnel, and variations in the wind tunnel model. This extensive set of high-quality surface pressure measurements is recommended for use in the calibration and validation of computational fluid dynamics codes for hypersonic flow conditions.

Physical Description

49 p.

Notes

OSTI as DE95014880

Source

  • 26. American Institute of Aeronautics and Astronautics (AIAA) computational fluid dynamics conference, San Diego, CA (United States), 19-22 Jun 1995

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  • Other: DE95014880
  • Report No.: SAND--95-1353C
  • Report No.: CONF-950634--6
  • Grant Number: AC04-94AL85000
  • DOI: 10.2172/101212 | External Link
  • Office of Scientific & Technical Information Report Number: 101212
  • Archival Resource Key: ark:/67531/metadc623901

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  • July 1, 1995

Added to The UNT Digital Library

  • June 16, 2015, 7:43 a.m.

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  • April 14, 2016, 1:17 p.m.

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Oberkampf, W.L.; Aeschliman, D.P.; Henfling, J.F. & Larson, D.E. Surface pressure measurements for CFD code validation in hypersonic flow, report, July 1, 1995; Albuquerque, New Mexico. (digital.library.unt.edu/ark:/67531/metadc623901/: accessed September 19, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.