Supersonic 2D Wing with Control Surfaces

Abstract

For some years ONERA, in collaboration with AEROSPATIALE, has undertaken research into improvement of CFD codcs, in the framework of studies on a new supersonic plane. The main goal has been to take unsteady effects, induced by movements of control surfaces such as spoilers or trailing edge flaps, into account with improved accuracy. For this purpose a wind tunnel test was carried out to provide an extensive database of unsteady behavior of control surfaces in supersonic conditions. ONERA has designed a generic 2D rigid model with two control surfaces: a spoiler and a trailing edge flap. These two control surfaces were moved in rotation by electro-hydraulic actuators, allowing an adjustment in static position as well as a harmonic excitation. A model with steady and unsteady pressure transducers, and accelerometers, was installed in thc ONERA 52 wind tunnel at Modane in March 1994 (figures 1 and 2).

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 2000
Accession Number
ADP010717

Entities

People

  • P. Naudin

Organizations

  • Office National d'Études et de Recherches Aérospatiales

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accelerometers
  • Accuracy
  • Actuators
  • Boundary Layer
  • Control Surfaces
  • Databases
  • Frequency
  • Hydraulic Actuators
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Pressure Transducers
  • Trailing Edges
  • Transducers
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Robotics and Automation.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow