Effects of Compressibility on the Characteristics of Five Airfoils

Abstract

Pressure distribution tests show that the effect of compressibility on flow for five airfoils at Mach number range of from 0.34 to 0.75. Schlieren photographs and graphs of pressure coefficient versus percent chord are included. Increment between critical Mach number and Mach number of normal force break was related to location of low-speed maximum negative pressure coefficient. For newer cambered airfoils, angle of zero lift shifted and pitching moment increased when Mach number was increased.

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Document Details

Document Type
Technical Report
Publication Date
Apr 25, 1947
Accession Number
ADA800558

Entities

People

  • Bernard N. Daley

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautics
  • Air Flow
  • Aircrafts
  • Airfoils
  • Compressive Properties
  • Computational Fluid Dynamics
  • Flow
  • Flow Separation
  • Low Drag
  • Mach Number
  • Measurement
  • Optical Equipment
  • Photographs
  • Pressure Distribution
  • Pressure Gradients
  • Shock Waves
  • Static Pressure

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Mathematics or Statistics