126
5 Supersonic Wind Tunnels
LDV velocity measurement in T200 wind
tunnel
S150 wind tunnel in closed test section and
free jet configuration
(a)
(b)
Fig. 5.13 T200 and S150 wind tunnels of CEAT-PROMETEE test platform in Poitiers (© Institut
PPRIME)
jet (maximum stagnation pressure of 3 bar, Mach number from 0.5 to 1.3, see
Fig. 5.13a).
– The S150 wind tunnel operates at a Mach number ranging from 0.8 to 2.8, with
a total pressure of up to 40 bars, in a test of 150 × 150 mm
2 or in a free jet. It is
used for shock wave/turbulence interaction studies or unsteady flows in launchers
propulsive nozzles (see Fig. 5.13b).
– The MARTEL bench (see Fig. 5.14) is devoted to supersonic jets at high temperature in steady state mode (up to Mach 3, stagnation temperature of 1800 °C)
or in transient mode generating a blast wave (Air-CH4 deflagration up to 200 bar
and 2200 °C) in an open semi-anechoic test hall.
Instrumentations consist of acoustic and velocity (LDV, 2D and 3D PIV), unsteady
pressure and density measurement techniques. Each bench allows continuous or
instantaneous schlieren visualisations also. These means allow the characterisation, understanding and modelling of supersonic flows for various subjects such
as basic aerodynamic instabilities, separated flows in nozzles, impinging jets, wall
boundary layers, shock wave/turbulence interaction, noise generation mechanisms,
compressibility effects on turbulence, etc.
5.3.4 Large Variable Mach Number Wind Tunnel
The S3MA wind tunnel at the ONERA centre in Modane-Avrieux, (see Fig. 5.15)
is a transonic/supersonic wind tunnel that can deliver flows from subsonic to supersonic. The different nozzle configurations are shown in Fig. 5.16. In subsonictransonic regimes, the wind tunnel is equipped with interchangeable test sections
of 0.56 m width with perforated walls on all four sides. In supersonic regime, the
wind tunnel is equipped with a nozzle of height 0.80 m and width 0.76 m.
The wind tunnel has a set of 5 supersonic nozzles whose nominal Mach number
ranges from 1.5 to 5.5. Intermediate values between Mach 4.5 and 5.5 can be realised
continuously by rotating the nozzle blocks so as to change the ratio of outlet area
5 Supersonic Wind Tunnels
LDV velocity measurement in T200 wind
tunnel
S150 wind tunnel in closed test section and
free jet configuration
(a)
(b)
Fig. 5.13 T200 and S150 wind tunnels of CEAT-PROMETEE test platform in Poitiers (© Institut
PPRIME)
jet (maximum stagnation pressure of 3 bar, Mach number from 0.5 to 1.3, see
Fig. 5.13a).
– The S150 wind tunnel operates at a Mach number ranging from 0.8 to 2.8, with
a total pressure of up to 40 bars, in a test of 150 × 150 mm
2 or in a free jet. It is
used for shock wave/turbulence interaction studies or unsteady flows in launchers
propulsive nozzles (see Fig. 5.13b).
– The MARTEL bench (see Fig. 5.14) is devoted to supersonic jets at high temperature in steady state mode (up to Mach 3, stagnation temperature of 1800 °C)
or in transient mode generating a blast wave (Air-CH4 deflagration up to 200 bar
and 2200 °C) in an open semi-anechoic test hall.
Instrumentations consist of acoustic and velocity (LDV, 2D and 3D PIV), unsteady
pressure and density measurement techniques. Each bench allows continuous or
instantaneous schlieren visualisations also. These means allow the characterisation, understanding and modelling of supersonic flows for various subjects such
as basic aerodynamic instabilities, separated flows in nozzles, impinging jets, wall
boundary layers, shock wave/turbulence interaction, noise generation mechanisms,
compressibility effects on turbulence, etc.
5.3.4 Large Variable Mach Number Wind Tunnel
The S3MA wind tunnel at the ONERA centre in Modane-Avrieux, (see Fig. 5.15)
is a transonic/supersonic wind tunnel that can deliver flows from subsonic to supersonic. The different nozzle configurations are shown in Fig. 5.16. In subsonictransonic regimes, the wind tunnel is equipped with interchangeable test sections
of 0.56 m width with perforated walls on all four sides. In supersonic regime, the
wind tunnel is equipped with a nozzle of height 0.80 m and width 0.76 m.
The wind tunnel has a set of 5 supersonic nozzles whose nominal Mach number
ranges from 1.5 to 5.5. Intermediate values between Mach 4.5 and 5.5 can be realised
continuously by rotating the nozzle blocks so as to change the ratio of outlet area