A SUMMARY OF DATA ON THE DIVISION OF LOADS FOR VARIOUS WING-FUSELAGE COMBINATIONS

Abstract

A summary has been made of the available experimental data on division of normal-force loads between the wing and fuselage of aircraft. Comparison of the experimental values with theoretical calculations which include interference effects show good agreement in general with the greatest differences occurring near a Mach number of 1.0. At high angles of attack, above the range of linear lift curves, the proportion of the total wing-fuselage load carried by the wing decreases and this effect occurs throughout the subsonic- and transonic-speed regions.

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Document Details

Document Type
Technical Report
Publication Date
Jun 08, 1953
Accession Number
AD0011322

Entities

People

  • Clarence L. Gillis

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aircrafts
  • Airplanes
  • Aspect Ratio
  • Delta Wings
  • Experimental Data
  • Free Fall Models
  • High Angles
  • Low Angles
  • Mach Number
  • Measurement
  • Models
  • Pressure Distribution
  • Pressure Measurement
  • Research Aircraft
  • Rocket Models
  • Swept Wings

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Mathematics or Statistics