WIND TUNNEL INVESTIGATION OF A 0.10-SCALE NORTH AMERICAN AVIATION AMSA INLET AT TRANSONIC AND SUPERSONIC MACH NUMBERS

Abstract

Test results are presented for a study on a 0.10-scale model of the North American Aviation proposed advanced manned strategic aircraft air vehicle. Inlets of various geometries were tested at several Mach numbers, angles of attack, and angles of yaw. Inlet performance in terms of compressor face total- pressure recovery and flow distortion is presented as a function of mass-flow ratio for various inlet geometries at several Mach numbers and model attitudes.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1967
Accession Number
AD0384742

Entities

People

  • H. E. Mcdill
  • J. F. Riddell

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Aircrafts
  • Boundaries
  • Boundary Layer
  • Boundary Layer Control
  • Compressors
  • Diffusers
  • Flow
  • Flow Fields
  • Geometry
  • Instrumentation
  • Layers
  • Mach Number
  • Mass Flow
  • Subsonic Diffusers
  • Supersonic Diffusers
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.
  • Aviation Science / Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow