Effect of Mach and Reynolds Numbers on Maximum Lift Coefficient

Abstract

Interrelated effects of Mach and Reynolds numbers on the maximum lift coefficient were investigated and compared with existing pertinent wind-tunnel data. Six pursuit-type airplanes embodying typical conventional and low-drag airfoils were selected, and flight data obtained in gradual stalls were made during turns or pull-ups with airplanes in clean condition over a range of Mach numbers from 0.15 to 0.72 and of Reynolds numbers from 4,400,000 to 19,500,000. Flight data were plotted and found to correlate closely with available wind-tunnel data.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1946
Accession Number
ADA801364

Entities

People

  • John R. Spreiter
  • Paul J. Steffen

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Aircrafts
  • Airfoils
  • Airplanes
  • Altitude
  • Boundary Layer
  • High Altitude
  • Layers
  • Low Drag
  • Low Drag Airfoils
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Two Dimensional
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Systems Analysis and Design