COMPARISON OF EXPERIMENTAL AND THEORETICAL STATIC AEROELASTIC LOADS AND DEFLECTIONS OF A THIN 45 DEGREE DELTA WING IN SUPERSONIC FLOW

Abstract

Wind-tunnel data showing the effects of static aeroelasticity are presented and compared with theory in the Mach number range 1.30 to 4.00. Calculated deformation, normal-force coefficients, and pitching-moment coefficients based on linearized potential theory are shown to compare favorably with the wind-tunnel results. Calculations are also made at Mach numbers of 3.00 and 4.00 based on piston theory and on a modification of piston theory. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1961
Accession Number
AD0265242

Entities

People

  • Floyd V. Bennett

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Aeroelasticity
  • Coefficients
  • Deflection
  • Delta Wings
  • Flow
  • Fluid Dynamics
  • Fluid Mechanics
  • Mach Number
  • Mechanics
  • Physics
  • Potential Theory
  • Supersonic Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow