Effects of Compressibility on the Flow Past Thick Airfoil Sections

Abstract

Six 3-inch-chord symmetrical air foils for propeller shanks having thickness ratios from 15 to 40 percent chord were tested at high subsonic Mach numbers. Schlieren photographs of each airfoil showed the flow characteristics to be very erratic at low supercritical speeds but improved at the highest supercritical speeds tested. Normal-force coefficients for the thick airfoils were very erratic at subcritical speeds but became regular at supercritical Mach numbers. The significant factor in improving airfoil performance was found to be the reduction of model thickness ratios.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1948
Accession Number
ADA801395

Entities

People

  • Bernard N. Daley
  • Milton D. Humphreys

Organizations

  • National Advisory Committee for Aeronautics

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautics
  • Air Flow
  • Cameras
  • Coefficients
  • Compressive Properties
  • Flow
  • Language
  • Mach Number
  • Optical Equipment
  • Photographs
  • Photography
  • Pressure Distribution
  • Shock
  • Shock Waves
  • Thickness
  • Transitions
  • Waves

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.