Effects of leading-edge blunting on the local heat transfer and pressure distributions over flat plates in supersonic flow Metadata

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Title

  • Main Title Effects of leading-edge blunting on the local heat transfer and pressure distributions over flat plates in supersonic flow
  • Series Title NACA Technical Notes

Creator

  • Author: Creager, Marcus O.
    Creator Type: Personal

Contributor

  • Originator: Ames Aeronautical Laboratory (U.S.)
    Contributor Type: Organization
    Contributor Info: National Advisory Committee for Aeronautics. Ames Aeronautical Lab

Date

  • Creation: 1957-12

Language

  • English

Description

  • Content Description: Report presenting an investigation of the effect of leading-edge thickness on the flow over flat plates with square and cylindrical blunting at Mach number 4 and free-stream Reynolds numbers per inch of 2380 and 6600. For test conditions, the bow shock wave was detached and leading-edge shape had no effect on surface pressures aft of two leading-edge thicknesses. Results regarding surface pressure, flow-field surveys, heat transfer, boundary-layer thickness, surface pressure distribution, local Mach number, local Reynolds number, and heat transfer are provided.
  • Physical Description: 54 p. : ill.

Subject

  • Keyword: flow characteristics
  • Keyword: aerodynamics
  • Keyword: pressure distributions

Collection

  • Name: National Advisory Committee for Aeronautics Collection
    Code: NACA
  • Name: Technical Report Archive and Image Library
    Code: TRAIL

Institution

  • Name: UNT Libraries Government Documents Department
    Code: UNTGD

Rights

  • Rights Access: public
  • Rights License: pd
  • Rights Statement: No Copyright, Unclassified, Unlimited, Publicly available

Resource Type

  • Report

Format

  • Text

Identifier

  • Accession or Local Control No: 93R14286
  • URL: http://hdl.handle.net/2060/19930084996
  • Report No.: NACA-TN-4142
  • Center for AeroSpace Information Number: 19930084996
  • Archival Resource Key: ark:/67531/metadc56855