Aerodynamic Test Facilities of ISL , Windtunnels, Shock tubes

Aerodynamic Test Facilities of ISL

Supersonic wind tunnel (blow-down): S 20 test section size: 20 cm x 20 cm velocity range: Mach 1.4 / 1.7 / 2.1 / 2.4 / 3 / 4 / 4.4 stagnation pressure: 0.4 – 1.6 MPa stagnation temperature: 290 K max. running time: 60 s
Supersonic wind tunnel (continuous): S 30 test section size: 30 cm x 30 cm velocity range: Mach 1,5 / 2 / 3 / 4 / 4.4 stagnation pressure: 0.2 - 1 MPa stagnation temperature: 320 K
Shock tunnels: STA und STB shock tube dimensions: Ø 100 mm, L ~ 22 m dump tank volumes: 10 und 20 m³ nozzles: Mach 3 / 3.5 / 4 / 4.5 / 6 / 8 / 10; exit diameters Ø 200 up to 410 mm typical model dimensions: Ø 60mm, L ~ 400 mm test conditions: atmospheric flight from ground up to 60 km altitude test time: 1 up to 4 ms

Transonic shock tube: STT shock tube dimensions: Ø 382 mm, L ~ 15 m measuring section: 233 mm x 236 mm typical model dimensions: Ø 25mm, L ~ 350 mm test conditions: Mach 0.3 up to 0.9 test time: 5 ms

Measurement techniques used:

measurement of steady and transient pressures
force and moment measurements using wind tunnel balances (wind tunnel)
measurement of aerodynamic coefficients using the free flight technique (shock tubes)
visualization by differential interferometry, shadow and schlieren photography