Comparison of the minimum drag of two versions of a modified delta-wing fighter as obtained from flight tests of rocket-boosted models and equivalent bodies between Mach numbers of 0.80 and 1.64 Metadata

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Title

  • Main Title Comparison of the minimum drag of two versions of a modified delta-wing fighter as obtained from flight tests of rocket-boosted models and equivalent bodies between Mach numbers of 0.80 and 1.64
  • Series Title NACA Research Memorandums

Creator

  • Author: Hasting, Earl C., Jr.
    Creator Type: Personal
  • Author: Mitcham, Grady L.
    Creator Type: Personal

Contributor

  • Originator: Langley Aeronautical Laboratory
    Contributor Type: Organization
    Contributor Info: National Advisory Committee for Aeronautics. Langley Aeronautical Lab

Date

  • Creation: 1956-09-24

Language

  • English

Description

  • Content Description: Report presenting an investigation to determine the reduction in minimum drag that could be obtained at supersonic speeds by redesigning the fuselage and reducing the wing and tail thickness of a modified delta-wing fighter-type airplane. Results regarding the mass-flow ratio, total-pressure recovery, and drag are provided.
  • Physical Description: 24 p. : ill.

Subject

  • Keyword: drag reduction
  • Keyword: aircraft design

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: 93R18706
  • URL: http://hdl.handle.net/2060/19930089416
  • Report No.: NACA-RM-L56E04
  • Center for AeroSpace Information Number: 19930089416
  • Archival Resource Key: ark:/67531/metadc62790