Testing Capabilities

ONERA wind tunnel facilities

 

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

 

F1

Fauga-Mauzac

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

 

F2

Fauga-Mauzac

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

CEPRA19

Saclay (DGA EP)

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

 

S1MA

Modane-Avrieux

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

 

S2MA

Modane-Avrieux

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

 

S3MA

Modane-Avrieux

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

S4A

Modane-Avrieux

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

S4B

Modane-Avrieux

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

BD2

Modane-Avrieux

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