Technical Guide to the UTAD-2 Wind Tunnel

3. Types of Wind Tunnel Tests

3.1 Three Component Force Testing

For this experiments model is mounted on external tree-component rider balance ABMK(t), which can work in manual balancing regime and as a strain gauge balance being a part of data acquisition and processing system.

3.2 Boundary Layer Problems Investigation

For education velocity distribution in boundary layer is investigated on a flat plate with different roughness using traversing probe. For scientific task of boundary layer control the specially prepared profile (Fig.3.1) is installed on balance. Close to the test section, the boundary layer control and visualization apparatus are mounted (fig. 3.2). Registration of both, loadings and visual picture are performed.

Figure 3.1 Test Model for Investigation of Flow Control with Streamwise Vortices	Figure 3.2 Experimental Rig for Flow Visualization in Controlled Boundary Layer

3.3 Certification of Anemometers and Wind Direction Meters

Testing and certification of means for measuring wind velocity and wind direction: vane and cup anemometers, a Pitot probes, five-hole and six-hole probes, etc. are performed. The flow velocity ranges from 3.5 to 28 m/sec, relative flow direction ranges from 0 to 360 deg.

Figure 3.3 Anemorhumbometer "Marc-60" in UTAD-2 Test Section

3.4 Working Through of New Types of Experimental Rigs, Data Acquisition and Processing Approaches for Low Speed Wind Tunnels

Continuous works on development and improvement of methods and methodology of aerodynamic investigations require conducting real tunnel runs. Taking into account that experiment cost in TAD-2 wind tunnel is relatively high, a somewhat part of works can be performed using inexpensive small wind tunnel. Such works as feasibility study of new methods of investigation and experimental rigs, working through the ergonomic features of new software concerning operator job and data representation, improvement of data processing methodology can be performed in UTAD-2 wind tunnel (Fig. 3.4).

Figure 3.4 A Model of Experimental Rig for Investigation of Unsteady Characteristics of Airplanes in UTAD-2 Wind Tunnel