Measurement in high-velocity wind tunnels
Experiments in high-speed velocity aerodynamics can be used to determine the forces effect on aircraft bodies in the flow stream or to detect flow fields both around the bodies and in flow channels of turbomachines (turbines, compressors). The measurements can be carried out using either pneumatic or optical methods. It is further possible to calibrate pneumatic velocity measurement systems, flow calibrations within the range from 0.1 to 16 kg/s, temperature calibrations in the flow fields, etc.
We offer
- Force/Moment measurement using internal and external multi-axis aerodynamic balances
- Pressure measurement on model surfaces
- Flow visualization by means of optical methods (Schlieren, interferometry, BOS), oil-flow visualization
- Flowfield measurement (various measurement techniques available: steady/unsteady pneumatic probes, PIV, HWA, HFA)
- Testing of linear blade cascades and turbine stators – measurements of pressure distributions on blades, fine probing of flowfields
- Testing of full turbine stages – determination of integral characteristics, fine probing of flowfields
- Measurement and calibration of mass flow rate – determination of flow-rate, loss, and frequency characteristics
- Calibration of various aerometric probes (pitot and static probes, directional probes, ice detectors, etc.)
Related infrastructure
INTERMITTENT SUCK-DOWN TRISONIC WIND TUNNELS
- Wind tunnels equipped with air dryer (free-stream relative humidity: 5-10%)
- Free-stream total pressure: 0.1 MPa
- Characteristic turbulence intensity: 0.4% – 0.8%
Tunnel designation |
A1 | A2 | A3 | A4 | A5 | C | M |
Test section [m] |
0.90 × 0.60 | 0,60 × 0.60 | 0.60 × 0.60 | 0.40 × 0.80 | 0.60 × 0.60 | 0.12 × 0.12 | 0.24 × 0.20 |
MACH number [1] |
0.20 – 0.75 | 0.30 – 1.10 | 1.40 – 2.10 | 0.15 – 0.93 | 0.10 – 0.94 | 0.20 – 1.00 | 0.20 – 2.10 |
REYNOLDS number [1] |
2 × 106 | 2 × 106 | 2 × 106 | 3 × 106 | 2 × 106 | — | 0.7 × 106 |
Test duration [s] |
6 – 8 | 6 – 8 | 6 – 8 | 6 – 8 | 6 – 8 | continuous | 10 – 60 |
WALL TYPE |
solid | perforated | solid | slotted | slotted | perforated | slotted |
WALL open-area ratio [%] |
22.5 | 0 – 10 | 0 – 10 | 0 – 20 | 0 – 20 |
MASS-FLOW CALIBRATION TUBE
- Measurement and calibration of mass flow rate by orifice plates according to ISO 5167
- Tube diameter: 512 mm
- Set of standardized orifice plates available, covering the mass-flow rate from 0.1 to 16 kg/s
- Measurement uncertainty on mass flow rate up to 0.6%
CLOSED-LOOP WIND TUNNELS
- Multifunction closed-loop wind tunnel allowing for independent control of Mach and Reynolds numbers
- Free-stream total pressure: 8 – 140 kPa
- Free-stream total temperature: 290 – 330 K
- Air humidity control
TEST SECTION FOR LINEAR BLADE CASCADES
- Free-stream isentropic Mach number: 0.2 – 2.5
- Test section: 0.45 × 0.1 m
- Available range of the inlet flow angle: ± 75° from the axis
- Free-stream turbulence intensity adjustable by exchangeable inlet grids – up to 10% (isotropic turbulence)
- Adjustable exit tailboards – solid, perforated, and slotted walls available
- Optical access
AXIAL TURBINE TEST RIG
- Pressure ratio: 1 – 8
- Dynamometers
- Froude Hoffman F249 – up to 15000 rpm
- Heenan Froude V-375 – up to 80000 rpm
- Free-stream turbulence intensity adjustable by exchangeable inlet grids – up to 10% (isotropic turbulence)
- Optical access
CALIBRATION WIND TUNEL
- Calibration of aerodynamic probes of various types (pneumatic, hot-wire, etc.)
- Free-stream Mach number: 0.2 – 1.1
- Exit nozzle diameter: 0.1 m
- Probe mounting allows covering the angle range of ± 90° in both vertical and horizontal planes
- Optical access
Supersonic closed-loop wind tunnel
- Free-stream Mach number: 0.2 – 3.5
- Closed test section of 0.25 x 0.25 m2
