EFFECTS OF SUCTION BOUNDARY-LAYER CONTROL ON THE PERFORMANCE OF A SHORT ANNULAR DIFFUSER WITH AN UPSTREAM TERMINAL NORMAL SHOCK

Abstract

A normal shock was positioned at distances ranging from 0.4 to 2.0 annulus gaps upstream from the diffuser entrance; the corresponding shock Mach number ranged from 1.40 to 1.47. Boundary layer suction flows as high as about 13 percent of the diffuser entrance flow were employed. The equivalent conical expansion angle of the diffuser was 10 degrees with about 5-percent suction flow, the over-all total pressure loss of the 10 degrees diffuser was less than that for a 5 degrees diffuser with no boundary-layer control. Pumping-power considerations indicated that suction-flow rates from 5 to 8 percent were economical relative to improved diffuser performance.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1962
Accession Number
AD0274329

Entities

People

  • Charles J. Shoemaker
  • John R. Henry

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Control
  • Computational Fluid Dynamics
  • Diffusers
  • Diffusion
  • Equations
  • Flow
  • Flow Rate
  • Layers
  • Mach Number
  • Mass Flow
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure
  • Subsonic Diffusers
  • Supersonic Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Mathematics or Statistics