5.3 Typical Supersonic Wind Tunnels
121
Fig. 5.8 Mach rhombus of a supersonic nozzle
5.3 Typical Supersonic Wind Tunnels
5.3.1 Basic Research Supersonic Wind Tunnel
The S8Ch supersonic wind tunnel at ONERA, Meudon is equipped with two
test sections with identical characteristics and utilises the same power supply and
common auxiliaries. Of an open circuit type, the wind tunnel operates continuously
at atmospheric conditions at the intake and a downstream suction generated by two
132 kW pumps. Before expansion, the atmospheric air is dried by passing it over a
bed of silica gel.
The facility has an auxiliary vacuum pump and a high-pressure air supply of
7 bar for the simulation of propulsion jets and to carry out flow control studies. The
test sections have a square section of 0.12 × 0.12 m
2 in supersonic (up to Mach
2) and rectangular section, 0.12 × 0.10 m
2 in transonic regime. Total pressure and
temperature are close to 10
5 Pa and 300 K respectively. Figure 5.9 shows one of the
test sections of the wind tunnel.
These facilities are dedicated to studies on shock wave/boundary layer interactions and shock wave/turbulence interactions, separation control, cavity flows, jets,
turbulence, laminarity, optical diagnostics, etc. A very complete set of measurement
and visualisation techniques can be used for a fine characterisation of flows: various pressure probes, and optical based systems such as PSP, PIV, LDV, infrared
thermography, schlieren and shadowgraph, surface flow visualisation. Figure 5.10
shows the test section in the half-nozzle configuration where the plane of symmetry
of the nozzle is replaced by a solid flat wall. The rotating cam located in the second
throat location makes it possible to periodically vary the position of the shock wave
in the test section for unsteady analysis.
121
Fig. 5.8 Mach rhombus of a supersonic nozzle
5.3 Typical Supersonic Wind Tunnels
5.3.1 Basic Research Supersonic Wind Tunnel
The S8Ch supersonic wind tunnel at ONERA, Meudon is equipped with two
test sections with identical characteristics and utilises the same power supply and
common auxiliaries. Of an open circuit type, the wind tunnel operates continuously
at atmospheric conditions at the intake and a downstream suction generated by two
132 kW pumps. Before expansion, the atmospheric air is dried by passing it over a
bed of silica gel.
The facility has an auxiliary vacuum pump and a high-pressure air supply of
7 bar for the simulation of propulsion jets and to carry out flow control studies. The
test sections have a square section of 0.12 × 0.12 m
2 in supersonic (up to Mach
2) and rectangular section, 0.12 × 0.10 m
2 in transonic regime. Total pressure and
temperature are close to 10
5 Pa and 300 K respectively. Figure 5.9 shows one of the
test sections of the wind tunnel.
These facilities are dedicated to studies on shock wave/boundary layer interactions and shock wave/turbulence interactions, separation control, cavity flows, jets,
turbulence, laminarity, optical diagnostics, etc. A very complete set of measurement
and visualisation techniques can be used for a fine characterisation of flows: various pressure probes, and optical based systems such as PSP, PIV, LDV, infrared
thermography, schlieren and shadowgraph, surface flow visualisation. Figure 5.10
shows the test section in the half-nozzle configuration where the plane of symmetry
of the nozzle is replaced by a solid flat wall. The rotating cam located in the second
throat location makes it possible to periodically vary the position of the shock wave
in the test section for unsteady analysis.