Internal Performance of a Variable Ramp Mixed Compression Intake at Mach 3.05,

Abstract

Results are presented of an experimental investigation into the performance of a two-dimensional mixed compression intake which featured focussed cowl compression matched to a discrete slot boundary layer bleed system. The tests were conducted at the intake design Mach number of 3.05. The design worked well in a two-dimensional sense, but the losses were exacerbated by three-dimensional viscous effects involving the sidewall boundary layers. Keywords: Air intakes, Boundary layer control, Supersonic inlets. (Australia)

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1985
Accession Number
ADA167005

Entities

People

  • S. A. Fisher

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Bleed Systems
  • Boundary Layer
  • Computational Fluid Dynamics
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Mechanics
  • Geometry
  • Mach Number
  • Pressure Distribution
  • Pressure Measurement
  • Propulsion Systems
  • Static Pressure
  • Subsonic Diffusers
  • Supersonic Diffusers
  • Three Dimensional
  • Turbines
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Calculus or Mathematical Analysis
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow