Effects of internal corner fillets on pressure recovery: Mass flow characteristics of scoop-type conical supersonic inlets Metadata

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Title

  • Main Title Effects of internal corner fillets on pressure recovery: Mass flow characteristics of scoop-type conical supersonic inlets
  • Series Title NACA Research Memorandums

Creator

  • Author: Valerino, Alfred S.
    Creator Type: Personal

Contributor

  • Originator: Lewis Flight Propulsion Laboratory
    Contributor Type: Organization
    Contributor Info: National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab

Date

  • Creation: 1952-12-08

Language

  • English

Description

  • Content Description: Report presenting an investigation in the 8- by 6-foot supersonic tunnel at a range of free-stream Mach numbers at zero angle of attack to determine the effects of internal corner fillets on the pressure recovery characteristics of twin-scoop conical-type inlets utilizing boundary layer removal and mounted on the RM-10 body. Without boundary layer removal, the use of fillets resulted in substantial improvements in pressure recoveries and near critical mass flows up to a certain Mach number.
  • Physical Description: 14 p. : ill.

Subject

  • Keyword: corner fillets
  • Keyword: aircraft inlets
  • Keyword: aerodynamics

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: 93R19627
  • URL: http://hdl.handle.net/2060/19930090337
  • Report No.: NACA-RM-E52J10
  • Center for AeroSpace Information Number: 19930090337
  • Archival Resource Key: ark:/67531/metadc64540