High-Speed Wind-Tunnel Tests of the NACA 23012 and 23012-64 Airfoils

Abstract

Force tests of the NACA 23012 and 23012-64 airfoils of 24-inch chord were made in the 8-foot high-speed wind tunnel at Mach numbers ranging from 0.10 to 0.75. Supplementary tests of a 5-inch-chord NACA 23012 airfoil were made in the 24-inch high-speed tunnel to obtain pitching-moment data at higher loadings than could be attained with the 8-foot tunnel models. The results, which were corrected as far as possible for tunnel-wall effects, who the variation with Mach number of lift, drag, and pitching-moment coefficients at angles of attack from -4 deg to 6 deg. At positive lifts the NACA 23012-64 airfoil had slightly higher critical speeds than the NACA 23012 airfoil. At the higher angles of attack in the supercritical speed region, large increases in the magnitude of the pitching-moment coefficient occurred.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1941
Accession Number
ADA801561

Entities

People

  • John V. Becker

Organizations

  • National Advisory Committee for Aeronautics

Tags

DTIC Thesaurus Topics

  • Accuracy
  • Coefficients
  • Compressible Flow
  • Flow
  • Mach Number
  • Measurement
  • Metal Plates
  • Pressure Distribution
  • Reynolds Number
  • Shock
  • Shock Waves
  • Static Pressure
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.