Trisonic wind tunnel
The trisonic wind tunnel allows to study the flight behaviour of objects in speed conditions going from the subsonic via the transsonic to the supersonic domain.
The installation offers the possibility to do low-cost testing by using models at reduced scale. The studied objects represent aircrafts, projectiles or missiles.
Numeric simulation allows the transposition of testing results to real scales.
Technical features
- Test section : 0.3 m x 0.4 m
- Mach range: M = 0.5 to 4.5 (continuously scalable)
- Reynolds number: up to 2 Mio using a sample diameter of 40 mm
- Pressure range: 1.1 bar to 20 bar
- Running time: between 30 s and 120 s depending on the Mach number and the dynamic pressure
- Up to 15 tests per day
High-Enthalpy Facilities
STA & STB
High enthalpy wind tunnels are used to produce realistic flow conditions (pressure, temperature) and allow to measure in a very short laps of time (1 to 2 ms) the effective stress to which missiles and projectiles are exposed in flight.
Technical features
- Enthalpy: up to 8 MJ/kg
- Inner diameter: 100 mm
- Length: about 22 ms
- Dump tank volume: 8.3 m³ or 17 m³
- Profiled nozzles: M 3, M 4.5, M 6, M 8, M 10
- Conical nozzles: M 10 - 12 - 14
Blast generator STT & Shock tube ST70B
These tubes are used to calibrate sensors and to study very fast phenomena like blasts, particle ignition etc.
Technical features
STT
- Diameter : 300 mm
- Length : about 13 m
- Flow speed: M 0.8 to M 1.2
Shock tube ST70B
- Diameter: 70 mm
- Length: about 10 m
- Flow speed: M 0.8 to M 1.2
Metrology
- Particle-Image-Velocimetry (PIV)
- Laser-Doppler-Velocimetry according to Smeets (LDV)
- Free-Flight-Force-Measurement (FFM)
- Pressure measurement: piezo-electric, piezo-resistive, pressure sensitive paints (PSP)
- Heat flow measurement: thin film sensors, coaxial thermocouples
- Visualisation: Schlieren, ombroscopy, differential interferometry, Coloured Background Oriented Schlieren (CBOS).
Two-stage light-gas guns
Two stage light gas guns are used to accelerate arbitrarily shaped projectiles to velocities up to > 7000 m/s (Ma 20) in order to study phenomena in free flight at hypersonic speeds.
Technical features
- Evacuated free-flight chamber to simulate differentatmospherical conditions
- Visualisations of air flows for aerodynamic studies up to Mach 20
- Determining the drag coef ficients in free flight
- Study on ablation behaviour
- Terminal ballistics for speeds > 7000 m/s
- Multi exposure flash x-ray imaging with 20 ns exposure times
