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Reference Number EP/V051326/1
Title Transonic Testing of passive flow control techniques in the Pilot European Transonic Cryogenic Wind Tunnel
Status Completed
Energy Categories ENERGY EFFICIENCY(Transport) 40%;
NOT ENERGY RELATED 60%;
Research Types Basic and strategic applied research 100%
Science and Technology Fields ENGINEERING AND TECHNOLOGY (Mechanical, Aeronautical and Manufacturing Engineering) 100%
UKERC Cross Cutting Characterisation Not Cross-cutting 100%
Principal Investigator Dr S Prince

Sch of Aerospace, Transport & Manufac
Cranfield University
Award Type Standard
Funding Source EPSRC
Start Date 30 April 2021
End Date 30 November 2021
Duration 7 months
Total Grant Value £21,932
Industrial Sectors Defence and Marine; Aerospace
Region East of England
Programme NC : Engineering
 
Investigators Principal Investigator Dr S Prince , Sch of Aerospace, Transport & Manufac, Cranfield University (99.999%)
  Other Investigator Dr D Di Pasquale , Sch of Aerospace, Transport & Manufac, Cranfield University (0.001%)
  Industrial Collaborator Project Contact , DSTL - Defence Science and Technology Laboratory (0.000%)
Project Contact , Airbus UK Ltd (0.000%)
Project Contact , European Transonic Windtunnel GmbH (0.000%)
Web Site
Objectives
Abstract The reduction of aircraft fuel burn, which results in reduced carbon emissions, is of vital importance to aviation and society in general. One way to do this is to reduce the aircraft drag - the air resistance to its flight. This is particularly true if aircraft are to operate at lower altitude where CO2 emissions do less harm, but where air density is higher. One way to do this is to employ passive (requiring no energy input) methods to control the airflow to ensure that the wing shock waves are weakened and do not cause the flow to diverge from the wing and become turbulent (separation). A consortia of UK Universities and representatives from industry (Airbus, BAe Systems, DSTL and the Aerospace Technology Institute) will undertake a campaign of fundamental experiments at the cryogenic European Transonic Wind Tunnel in Cologne, to investigate whether strips of small scale roughness on a small scale, but representative wing section, can effectively act to weaken the wing shock wave
Publications (none)
Final Report (none)
Added to Database 20/09/21