ONERA Wind Tunnel Division offers a large panel of wind tunnels, for aerodynamic and acoustic test, covering very low Mach number to hypersonic Mach numbers.
Wind tunnels are located in 3 different areas in France: Modane-Avrieux, Le Fauga-Mauzac (near Toulouse) and Saclay (close to Paris).
- 5 continuous wind tunnel covering Low speed (few m/s) up to Mach 3.1,
- 3 blow-down wind tunnels covering Mach 0.1 up to Mach 12,
- 2 additional wind tunnels for specific applications.
A wind tunnel for every type of test
|
Facility |
Type Power |
Test section L x H |
Velocity/ Mach number |
Reynolds number based on 0.1ѴA |
Main applications Optical measurement capabilities: Particle Image Velocimetry Pressure Sensitive Paints Model Deformation Measurement |
|
Continuous Pressurized 9.5 MW |
Cart 1 4.5 x 3.5 m Cart 2/4 4.5 x 3.5 m Cart 3 4.5 x 3.5 m |
M ≤ 0.36 ≤ 123 m/s M ≤ 0.36 123 m/s M ≤ 0.36 ≤ 123 m/s |
8 106 8 106 8 106 |
Model mounts: sting, 3 masts, single mast ½ models with engine simulators Ground effects Air inlets, with or without ground effect PIV, PSP, MDM |
|
|
Continuous Atmospheric 0.75 MW |
1.4 x 1.8 m |
≤ 100 m/sec |
1.106 |
Research programs for air, land and sea transport Blade profile optimization for wind turbine Remotely controlled bench for optical measurement systems with large displacements : 0.5 x 0.6 x 1 m Remotely controlled probing device (pressure, temperature, hot wire and microphone) : 0.45 x 0.3 x 1.12 m / 360° LDV, PIV, PSP, MDM, ThIR , acoustic antenna |
|
|
Aeroacoustic Continuous Atmospheric 7 MW |
Open jet Ø 2 m Open jet Ø3 m |
120 m/s 60 m/s |
1.3 106 |
Aeroacoustic testing with or without jet simulation PIV, PSP, MDM |
|
|
Continuous Atmospheric 88 MW |
Transonic 3 carts Ø 8 m |
Mach < 1 |
7 106 |
½ models, with engine simulators Model mounts: sting or mast Laminar flow tests Air inlets Captive trajectory system Rotating wings, rotors Aeroacoustic measurement capabilities Sting interferences determined with CFD PSP, MDM |
|
|
Continuous pressurized 55 MW |
Transonic 1.75 x 1.77 m Supersonic 1.75 x 1.93 m |
M ≤ 1.5 1.5 ≤ M ≤ 3.0 |
5.4 106 4.0 106 |
Model mounts: sting or wall ½ models with engine simulators Captive trajectories/stores release Air inlets Simulation of hot or cold jets Dynamic stability PIV, PSP, MDM |
|
|
Blow down |
0.56 x 0.78 m 0.76 x 0.80 m |
0.1 ≤ M ≤ 1.3 1.65 ≤ M ≤ 3.8 + fixed nozzles Mach 2/3.4/4.5/5.5 et 6.05 |
3.5 106 3.2 106 |
Launchers and missiles 2-D profiles Mounted on sting or on wall Precipitation erosion Air inlets Jet simulation PSP |
|
|
Blow down |
Ø 0.68 m Ø 1 m Ø 1 m |
Hypersonic |
0.35-1.7 106 |
Load, pressure and thermal flux measurement Coating thermal and mechanical resistance tests Aerothermal erosion Air inlets and ramjets |
|
|
Model engine calibration rig |
4 '' bench 9 '' bench |
Simulated Mach ≤ 0.9 |
|
Thrust/flowrate calibration of flow-through or motorized nacelles Direct or reverse jet configuration Laser velocimetry and IR thermographic measurements |
|
|
Dynalpy test bench for nozzle |
|
|
|
Flow features : Primary flow: 16kg/s, T ≤ 1150 K Secondary flow: 14 kg/s, T ≤ 450 K Tertiary flow: 0.7 kg/s Thrust (13,500 N), side loads, temperatures, pressure and flowrate measurements |
|
|
R4-1 Modane-Avrieux |
Blow down |
Ø 600 mm |
Mach < 1 |
|
Air intake testing research programs |
Technical documentation