THE INFLUENCE OF AEROELASTICITY ON THE LONGITUDINAL STABILITY OF A SWEPT WING SUBSONIC TRANSPORT AIRCRAFT

Abstract

A numerical treatment of the influence of the aeroelastic deformations on the longitudinal stability and control characteristics of an aircraft with a swept-back wing of large aspect ratio is carried out for the sub-critical speed range. Only the deformation of the wing and the bending of the fuselage have been taken into consideration. The method used to calculate the deformations of the wing is based on the superposition of a number of pre- selected load distributions (A Superposition Method for Calculating the Aeroelastic Behavior of Swept Wings, Aug. 1951, by R. B. Brown et alii). An investigation of the accuracy of the method has been made by comparing the numerical results with those of another more exact method which proved the reliability of the present method. As a result of the study it was found that the stability and control of the aircraft are only slightly affected by the aeroelastic deformation.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1961
Accession Number
AD0448909

Entities

People

  • C. M. Kalkman

Organizations

  • AGARD

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aerodynamic Loading
  • Aeroelasticity
  • Aircrafts
  • Airframes
  • Airplanes
  • Dynamic Pressure
  • Fluid Dynamics
  • Horizontal Stabilizers
  • Incompressible Flow
  • Load Distribution
  • Mach Number
  • National Security
  • Swept Wings
  • Sweptback Wings
  • United States
  • Wing Tips

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Structural Dynamics.