Aerodynamic research
Each student in Aerospace Engineering is required to do a number of exercises in the Faculty’s wind tunnel laboratories. These exercises range from measuring the lift on an aerofoil in a flow of 50 m/sec to measuring the drag from a delta wing in a flow of two times the speed of sound (Mach 2).
A combination of basic and applied research is carried out using these wind tunnels. The focus of basic research is the analysis of aerodynamic phenomena that occur in flows around aircraft and spacecraft. The applied research deals with aerodynamic problems of direct relevance to aerospace technology.
A list of wind tunnels:
Name | Test section | Seed range |
Subsonic Low Turbulence Tunnel | 1.25 x 1.80 m | 120 m/s |
Subsonic Boundary Layer Tunnel | 1.25 x 0.25 m | 50 m/s |
TST-27 Transsonic / Supersonic Wind Tunnel | 0.4 x 0.4 m | 35 m/s |
ST-15 Supersonic Wind Tunnel | 150 x 150 mm | Mach 0.7 - 3.0 |
HTFD Hypersonic Wind Tunnel | 350 mm Ø | Mach 6.0 - 11.0 |
ST-4 Supersonic Wind Tunnel | 40 x 40 mm | Mach 0.5 - 3.0 |
ST-3 Supersonic Wind Tunnel | 30 x 30 mm | Mach 1.5 - 3.5
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More details about the different wind tunnels can be found on the website of the Aerodynamics chair.
