INVESTIGATION OF THE AIR-FLOW-REGULATION CHARACTERISTICS OF A TRANSLATING-SPIKE INLET WITH TWO OBLIQUE SHOCKS FROM MACH 1.6 TO 2.0

Abstract

The air-flow regulation and pressure recovery of a translating-cone inlet with a 15 deg conical half-angle and a 10 deg additional compression was investigated for a range of spike positions at Mach numbers of 0.6 and 1.6 to 2.0 at zero angle of attack.

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Document Details

Document Type
Technical Report
Publication Date
Jul 24, 1956
Accession Number
AD0102312

Entities

People

  • J. C. Nettles

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Air Flow
  • Compression
  • Diameters
  • Diffusers
  • Engines
  • Flow
  • Free Stream
  • Government Procurement
  • Governments
  • Mach Number
  • Mass Flow
  • Pressure Transducers
  • Recovery
  • Regulations
  • Subsonic Diffusers
  • Turbojet Engines
  • United States Government

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Combustion and Flow Dynamics.