Wind Tunnel Investigation of a 1/8-Scale AMSA Aircraft-Inlet Model at Transonic and Supersonic Mach Numbers

Abstract

Test results are presented for a 1/8-scale inlet model of a proposed AMSA air induction system at transonic and supersonic Mach numbers. The effects of spike bleed pattern and inlet orientation are presented. Compressor-face total-pressure recovery and flow distortion data are presented as a function of spike position, compressor-face mass-flow ratio, spike boundary-layer bleed mass-flow ratio, angle of attack, angle of sideslip, and free-stream Mach number.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1967
Accession Number
AD0385450

Entities

People

  • Lawrence L. Galigher

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Airplanes
  • Boundaries
  • Boundary Layer
  • Compressors
  • Flow
  • Free Stream
  • Induction Systems
  • Instrumentation
  • Mach Number
  • Mass Flow
  • Measurement
  • Pressure Measurement
  • Test And Evaluation
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow