The two-dimensional wind tunnel is used to test aerofoil sections at speeds between Mach 0.3 and 0.87. The tunnel test section is 0.2m (8in) by 0.46m (18in). The typical model chord length is 0.127m (5in).
The maximum unit Reynolds number is 55 million per metre. The stagnation pressure ranges between 1.5 and 4.0 bars atmospheric pressure.
The incidence range for models is -11° to +20°.
The 2-Dimensional tunnel is mainly used for dynamic testing and analysis of helicopter rotor blade section performance. The model is mounted in the Enhancing Rate Pitching System (ERPS) which is used to simulate the rotor blade dynamics to assess: dynamic stall of the retreating blade, and shock induced separation of the advancing blade. The ERPS is driven at different frequency and incidence rates to simulate the aerodynamics of the advancing and retreating helicopter rotors.
The model is filled with 39 Dynamic Pressure Transducers (Kulites) measuring chordwise pressure distribution which are integrated to give sectional CN and CM.
The 2-D tunnel can also be used to measure the steady-state lift, pitching moment and drag of aerofoil sections.