Design and Testing of a Morphing Wing for an Experimental UAV

Abstract

A morphing concept for wing drag reduction for a small UAV is presented. The results of a computational assessment of the morphing concept benefits are shown. 14% to 30% drag reduction in different flight stages serve as motivation for the construction of a prototype. Design requirements of the morphing mechanism structure are pointed out and constructive solutions are shown. Feasibility and functionality of the constructive solutions are discussed briefly. Wind tunnel test results are not available yet.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 2007
Accession Number
ADA478692

Entities

People

  • A. Suleman
  • F. Lau
  • J. Vale
  • P. Aleixo
  • P. Gamboa

Organizations

  • University of Beira Interior

Tags

Communities of Interest

  • Air Platforms
  • Autonomy

DTIC Thesaurus Topics

  • Abstracts
  • Aerodynamic Characteristics
  • Aerodynamic Configurations
  • Aerodynamic Loading
  • Aircraft Wings
  • Aircrafts
  • Composite Materials
  • Construction
  • Drag
  • Drag Reduction
  • Geometry
  • Models
  • Morphing Wings
  • Spars
  • Unmanned Aerial Vehicles
  • Wind Tunnel Tests
  • Wind Tunnels

Readers

  • Database Systems and Applications
  • Fluid Mechanics and Fluid Dynamics.
  • Internal Combustion Engine (ICE) Technology.