Effect of Mach Number on the Maximum Lift and Buffeting Boundary Determined in Flight on a North American P-51D Airplane

Abstract

Abrupt and gradual stalls were made in Mach ranges of 0.21-0.63 and 0.41-0.65 respectively. Abrupt pull-ups were made through Mach range of 0.21-0.30. Mach number greatly affected maximum lift coefficient and buffeting boundary line. Buffeting boundary was defined by maximum lift coefficient only up to M = 0.64. Above M = 0.12, calculations lost their agreement with flight data. Gradual stalls showed same effect of Mach number as abrupt stalls.

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Document Details

Document Type
Technical Report
Publication Date
Jun 12, 1947
Accession Number
ADA800868

Entities

People

  • John P. Mayer

Organizations

  • Langley Research Center

Tags

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Agreements
  • Aircrafts
  • Airfoils
  • Airplanes
  • Airspeed
  • Altitude
  • Boundaries
  • Buffeting
  • Coefficients
  • Laboratory Tests
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Reynolds Number
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.