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European Transonic Windtunnel (ETW)
Hosting Legal Entity
Self-standing RI
Legal Status
International or intergovernmental organisation or framework
Ernst-Mach-Strasse, ETW - European Transonic Windtunnel GmbH, Cologne, PO: 51147, NRW (Germany)
Type Of RI
Coordinating Country
Participating Countries
United Kingdom
Current Status:
Operational since 1995
Scientific Description
The European Transonic Wind Tunnel (ETW) was designed and constructed by the four European countries France, Germany, Great Britain and The Netherlands. It is operated based on a non-profit policy. ETW is located in Cologne, Germany.European researchers and engineers harness ETW’s capabilities for advancing aeronautical science into aircraft innovation by accessing real-flight conditions in this cutting edge ground-test laboratory. Training opportunities for researchers and engineers are provided.ETW is the worldwide leading wind tunnel for testing aircraft at real flight conditions. Aircraft performance and their flight envelope limits can be accurately determined with unique quality at ETW long before flight testing of a first prototype. This enables significant reduction in the technical and economic risks associated with the development of new aircraft. Manufacturers from all over the world take advantage of the exceptional features of this high-tech facility enhancing the performance, economic viability, and environmental friendliness of their future aircraft.ETW operation and access complies with the ISO9001 quality management standard.

RI Keywords
Liquid nitrogen, Wind tunnel measurements, Aeroelastic, Flight reynolds-number simulation, Aerodynamics, Wind tunnel measurement technique, Cryogenic temperatures, Aeroacoustics
RI Category
Aerospace and aerodynamics research facilities
Scientific Domain
Engineering and Energy
High-/Flight-Reynolds Number Wind-Tunnel Testing at ETW

ETW offers worldwide experimental wind tunnel investigations focussing on aerodynamic and aeroelastic measurements on lifting bodies in the subsonic, transonic or supersonic speed range up to Mach-numbers of 1.35. Taking the benefit of the cryogenic technique is allowing for an extremely accurate simulation of flow effects at high Reynolds-numbers of up to 90 Million. Beside classic measurements of forces and moments additional techniques are available for analyses of the origination and development of aerodynamic processes. The application and operation of non-intrusive techniques is here the most favoured approach.

Pressure Measurement by Pressure Sensitive Paint
Pressure Measurement System
Flow field analysis by Particle-Image Velocimetry
Transition Detection by Temperature Sensitive Paint
Unsteady Pressure Measurement System
Optical Deformation Measurement System
Balances for Force & Moment Measurements
European Windtunnel Association
Date of last update: 08/03/2018
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