Effects of Mach Number and Reynolds Number on the Maximum Lift Coefficient of a Wing of NACA 230 Series Airfoil Sections

Abstract

Wing was tested with full-span, partial-span, or split flaps deflected 60 Degrees and without flaps. Chordwise pressure-distribution measurements were made for all flap configurations.. Peak values of maximum lift coefficient were obtained at relatively low free-stream Mach numbers and, before critical Mach number was reached, were almost entirely dependent on Reynolds Number. Lift coefficient increased by increasing Mach number or deflecting flaps while critical pressure coefficient was reached at lower free-stream Mach numbers.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1947
Accession Number
ADA800630

Entities

People

  • G. C. Furlong
  • James E. Fitzpatrick

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamics
  • Aeronautics
  • Airfoils
  • Boundary Layer
  • Flow
  • Free Stream
  • Leading Edges
  • Mach Number
  • Measurement
  • Peak Values
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Split Flaps
  • Surfaces
  • Turbulent Boundary Layer
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.