Experimental Validation of an Aeroelastically Scaled Sensorcraft Model

Abstract

This report results from a contract tasking University of Liverpool as follows: 1. Development of a scaled Finite Element model of the wind tunnel model. 2. Design and manufacture of wind tunnel model of a half-span sensorcraft with load alleviation device on the outer section of the wing static and dynamic laboratory tests. 3. Static tests to investigate non-linear deflection behaviour (with AFIT). 4. Static and dynamic wind tunnel tests to investigate performance of gust load alleviation device. 5. Comparison between numerical predictions and experimental tests 6. Interim and final reporting.

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Document Details

Document Type
Technical Report
Publication Date
Aug 05, 2009
Accession Number
ADA521205

Entities

People

  • Jonathan E. Cooper

Organizations

  • University of Liverpool

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aircrafts
  • Deflection
  • Equations Of Motion
  • Gust Loads
  • Gusts
  • Laboratory Tests
  • Leading Edges
  • Mach Number
  • Mechanics
  • Models
  • Optimization
  • Resonant Frequency
  • Wind
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Engineering

Readers

  • Aerodynamics/Aeronautics.
  • Technical Research and Report Writing.