An Investigation of the Low-Speed Characteristics of Two Sharp-Edge Supersonic Inlets Designed for Essentially External Supersonic Compression

Abstract

Wind-tunnel investigation was made on supersonic air inlets to obtain information on surface-pressure, drag, and pressure-recovery characteristics. Two types of sharp-edged annular inlets tested were designed for Mach numbers of from 1 to 3. Surface pressure distribution, minimum surface pressures, and critical Mach numbers were tested. It is concluded that sharp pressure peaks occur outside small velocity range, separation is confined to bubble at leading edge, external drag is higher than on round-edged cowlings, and better pressure distribution is possible with slight modification.

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Document Details

Document Type
Technical Report
Publication Date
Jun 06, 1947
Accession Number
ADA800551

Entities

People

  • John S. Dennard

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Abstracts
  • Aeronautical Laboratories
  • Aeronautics
  • Boundary Layer
  • Compression
  • Flight Speeds
  • High Pressure
  • Leading Edges
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure
  • Subsonic Flight
  • Supersonic Flight
  • Supersonic Inlets
  • Surfaces

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow