The Laval wind tunnel can has a rectangular test section of dimensions 40mm x 181 mm x 400 mm. Typical freestream velocities can go up to 160 m/s or a Mach number of M=0.5, i.e. a mass flow rate of about 1.5 kg/s. A boundary layer based Reynolds number of 700 000 is thus attainable. The freestream flow can be heated to a temperature of 120°C by a steam heat exchanger which can be accurately regulated and controlled. A water-cooled heat exchanger extracts the heat from the freestream downstream of the test section before it returns in a closed loop to the compressor. The boundary layer thickness of the flow is controlled by a suction arrangement. The boundary layer is sucked off through multiple, 1.2 mm diameter, discrete holes of covering an area of 60 mm x 180 mm. The extracted air is fed back into the loop downstream.

In order to study mixing and jet impingement a secondary air supply also exists to provide air which can be cryogenically cooled down to –40°C. This cooled air can be injected through different hole arrangements to study various jet-in-crossflow configurations. The different temperatures between the injectant and the freestream are required to mimic the density ratios typically found in jet engines. In order to study unsteady effects the cool air can also be pulsated via an in-house designed pulsator, with frequencies up to 500 Hz.

The wind tunnel walls have access for intrusive probe measurements as well as for PIV and IR thermography.