Centrum Technologii Lotniczych

Aerodynamics Research Laboratory

The Aerodynamics Research Laboratory is a part of the Center of New Technologies (CNT). As part of its activities it conducts scientific and research & development work related to applied aerodynamics, which is unique both in Poland, as well as on global scale.

The laboratory operates 5 wind tunnels, which includes the largest and the fastest wind tunnels in the Central-Eastern Europe. The center has one of the world’s most advanced research infrastructure in terms of applied aerodynamics . Upgrade works implemented in the Laboratory, have been introduced in response to international market demand in the area of fluid mechanics and sophisticated requirements of economic and industrial sectors.

Activities of the laboratory cover high-priority areas with strategic importance in terms of the research work directions, such as:

1. Environment
   • Environmental studies of wind resistance
2. Energy and its resources
   • aerodynamic studies of wind turbines, which are the latest solutions in energy-generation technologies
   • aerodynamic studies of power units and cooling towers
3. Transport infrastructure
   • aerodynamic studies of various means of land and air transport

The scope of the conducted work includes:

• aerodynamic research for Polish and international aviation industry,

• research & development work related to applied aerodynamics, which are also conducted within confines of European Framework Programmes,

• wind tunnel studies of non-aeronautical aerodynamics conducted for automotive, construction, energy, space technology, sports, shipbuilding and military sectors,

• commercial research studies for domestic and international customers

• close cooperation with aviation industry leaders, technical universities and entities from the R&D sector

The Aerodynamics Research Laboratory employs highly qualified personnel with technical skills and expertise necessary for proper delivery of all works.

The mission of the Aerodynamics Research Laboratory is to provide top-class research services for the international scientific research market.

The Aerodynamics Research Laboratory has implemented:

• a Quality Management System compatible with the standard requirements

• Laboratory Management System compatible with the requirements of the Internal Control System Criteria standard

Technical results of research obtained in the laboratory are recognized both by the International Standard Organization ISO as well as by International Laboratory Accreditation Cooperation

Since 22nd October 1997, the Applied Aerodynamic Laboratory has the Accreditation Certificate no. AB 129 issued by Polish Centre for Accreditation .

Low Speed Wind Tunnel (5 m)

Upgraded in 2015, this low-velocity wind tunnel is a closed-loop tunnel, with an open measuring space, which has 5 meters in diameter and is 6.5 meters long. Dimensions, engine power (5.6 MW) and wind speed (90 m/s) place this tunnel among world’s leading low-velocity wind tunnels.

Additionally the wind tunnel is equipped with an innovative IPW400 and IPW80 secondary flow systems generating additional air flows, with the maximum mass flow rates of 45 kg/s and 2 kg/s, accordingly. The IPW80 system allows also the medium temperature to be raised to 250^oC. This unique system permits testing of aircraft engines’ internal components or their models under simulated takeoff and landing conditions and in increased exhaust gases temperatures.

As part of the Aerodynamics Research Laboratory research activities, the following tests are performed in the wind tunnels:

• measurements of forces and moments,

• measurements of pressure distributions,

• flow visualizations.

These tests are performed on models of aircraft and helicopter parts (fuselages, rudders and stabilizers, main and tail rotors), buildings, navy ships, cars, trains and two-dimensional profiles.

Tests involving measurements of dynamic stability, aeroelastic model deformation and laminar flow parameters are also performed.

The wind tunnel allows testing of aircraft models with wingspans up to 4 m, non-aircraft models, which generate aerodynamic drag (residential and public buildings, bridges, industrial structures) with heights of up to 3 m and cross-section area (perpendicular to the flow direction) of up to 2.5 sq. m and models of rotors up to 3 m in diameter.

For tests not related to aviation, a special flat plate is installed in the measuring area. Correct velocity and turbulent airflow profiles are achieved by relevant modifications of this plate surface.

Trisonic Wind Tunnel

The Trisonic Wind Tunnel is in operation since 1965. The tunnel is a blow-down type with partial recirculation of the flow and can be operated in all three regimes, subsonic, transonic and supersonic. Mach number can be changed in range M = 0.2 – 2.3.

The tunnel is supplied from two spherical compressed air tanks with the combined volume of 2880 m³ and maximum pressure of 6.5 atm. The air is compressed using two 2000 kW centrifugal compressors and is appropriately purified and dried.

The average operating time of the wind tunnel, is:

• for supersonic Mach velocities – about 3 minutes,
• for subsonic Mach velocities – about 5 minutes,
• for low subsonic Mach velocities (0.3 – 0.5 Mach) – for over ten minutes.

Measurements are performed in a measuring chamber with the diagonal cross section of 0.6 x 0.6 m, which makes this wind tunnel one of the largest and fastest facilities of this type in Poland.

Capabilities:

• wind tunnel tests of aircraft models, the measurement of their aerodynamic characteristics and pressure distributions for Mach number M = 0.2 ÷ 2.3,
• aerodynamic load measurements on airframe part models (wings, horizontal and vertical stabilizers, control surfaces, external pods and stores, etc.),
• hinge-moment measurements for tail units,
• buffeting boundary determination and its intensity in a wide range of flow velocities,
• oil flow visualisation and Schlieren method of visualisation (coloured and b/w),
• airfoils aerodynamic characteristics,
• the aerodynamic design of aircraft wings, profiles (also with a high lift coefficient),
• unsteady pressure measurements with control and actuation mechanism for flap and profile oscillations.

Low Speed Wind Tunnel (1.5 m)

The Low Speed Wind Tunnel is a closed-circuit, continuous-flow low speed tunnel with the 1.5 meter diameter open test section. The wind tunnel is powered by a 55 kW electric engine with 4-blade, constant-speed fan. The maximum velocity of the medium is 40 m/s. Capabilities:

• balance tests: models of 2D airfoils and 3D objects,
• roughness effect tests,
• optimisation of flap geometry and position,
• hinge-moment optimisation for ailerons and tail units,
• pressure distribution tests,
• tufts and minitufts with UV-light flow visualisations,
• smoke flow visualisation,
• PIV 3D flow visualization.

Low Turbulence Wind Tunnel TMT

The Low Turbulence Wind Tunne is an atmospheric, open-circuit tunnel with two linked, closed, rectangular test sections. The front test section (1.75×2.28 m) is dedi-cated for the investigations for the airflow speed up to 8 m/s. The rear test section has smaller dimensions (0.5×0.65 m) but the airflow speed of 85 m/s may be achieved. The wind tunnel is powered by two direct-current engines, rated 5.1 kW and 64 kW, which are selected depending on the required agent velocity (40 m/s). Capabilities: In the TMT wind tunnel may be conducted:

• the pressure distribution tests,
• strain gage balance tests,
• CTA tests or a flow visualisation (smoke, oil or PIV). The tests may concern laminar airfoils, airplanes, helicopters, ships or any other object which require low turbulence of the airflow.

Supersonic Wind Tunnel

The Supersonic Wind Tunnel is a blow-down type with a closed test chamber of 0.15 x 0.15 m. The velocity range is M = 1.22 – 3.5. The tunnel is used for research on aerodynamic phenomena related to supersonic flow like: boundary layer interaction with a shock wave.

Contact:

Head of Aerodynamics Research Laboratory
Grzegorz Krysztofiak M.Sc. Eng.
Phone: (+48) 0 22 846 00 11 ext. 204
Fax: (+48) 0 22 846 44 32
E-mail:grzegorz.krysztofiak[at]ilot.lukasiewicz.gov.pl

Robert Placek M.Sc. Eng.
Phone: (48-22) 846 00 11 ext. 360
E-mail: robert.placek[at]ilot.lukasiewicz.gov.pl