Transonic Pitch Damping of a Delta Wing Aircraft Determined from Flight Measurements,

Abstract

A flight investigation aimed mainly at determining the pitch damping of a 60 degree Delta wing aircraft between M = 0.7 and M = 1.2 has been undertaken. Flight tests were conducted by ARDU and the measurements obtained have been successfully analysed at ARL using a modified Newton-Raphson parameter estimation procedure. The results for pitch damping as well as other longitudinal aerodynamic derivatives have been compared with wind tunnel and/or theoretical estimates. Further information has also been gained relating to the necessary conditions for successful extraction of parameters from flight data. The parameter estimation procedure has proved to be an effective analysis method even when only a modest amount of flight data, obtained using a relatively simple instrumentation package, has been available. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1979
Accession Number
ADA087771

Entities

People

  • R. A. Feik

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accelerometers
  • Air Force
  • Aircrafts
  • Angle Of Incidence
  • Center Of Gravity
  • Computer Programs
  • Delta Wings
  • Engineering
  • Equations
  • Equations Of State
  • Instrumentation
  • Mach Number
  • Mathematical Models
  • Measurement
  • Measuring Instruments
  • Standards
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Aerospace Engineering
  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.