The INCAS Trisonic Wind Tunnel is a blowdown type experimental Installation, with an experimental chamber measuring 1.2m x 1.2m.
The tunnel was introduced in 1978 and has the following characteristics:
– Mach number range: [0.1, 3.5];
– Experimental room with solid walls for subsonic / supersonic 1.2 m x 1.2 m;
– Transonic 3D experience room with perforated walls, 1.2 m x 1.2 m, holes inclined at 60 degrees, porosity varying between 0.35% and 9.1%;
– Two-dimensional experience room, 0.48 m x 1.2 m;
– Flexible nozzle for Mach numbers from 1.1 to 3.5;
– Reynolds maximum 100 × 106 in the three-dimensional experience chambers, maximum 150 × 106 in the two-dimensional experience chamber;
– The flow regime is regulated by means of the control valve, which maintains the stagnation pressure at the programmed value.
The tunnel is generally used to determine the aerodynamic performance of models (measuring aerodynamic forces and moments and pressure distributions) and visualizations using a special paint or Schlieren installation.
Depending on the working conditions, 5-8 runs can be achieved each day. The scale and dimensions of the model depend on the regime, the maximum loads allowed for the model mounting system and for the balance as well as the aerodynamic locking (most sensitive in transonic mode).