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[Low Speed To Hypersonic]
ASE has designed wind tunnel facilities from very low subsonic to very high hypersonic speeds. This wide capability means that ASE has the experience to provide your facility, whatever its speed range.
Wide Temperature Range
[Cryogenic To High Enthalpy]
Facilities of every temperature range have been designed by ASE. Examples include the NTF (National Transonic Facility) which operates at temperatures as low as -320o F (77K) and storage heaters designed for up to 4000 F (2480K). We also regularly design facilities for ambient conditions and more conventional ratings, such as the heat exchanger for the NASA IRT (Icing Research Tunnel) at the NASA Glenn Research Center.
Wide Pressure Range
[Full Vacuum To 2000 Atmos.]
ASASE has designed facilities and equipment over a range of pressures from essentially full vacuum (AEDC J6 rocket test cell diffusers and ejector and CIRA Plasma heat exchanger) to 5000 atm (HEG Free Piston Shock Tunnel in Goettigen, Germany). As designers and builders of more conventional facilities, ASE has provided cost effective facilities for all levels of pressure.
Various Drive Sources
[Continuous, Blowdown, Mixed]
Wind tunnels are often described by the method used to drive the test gas. The usual method is with the use of fans or compressors to drive continuous tunnels. For some applications this cannot be done due to the high power needed. In these cases Blowdown methods might be used; the test gas from high pressure reservoirs flows past the model for a time determined by the storage capacity and pressure. The T1500 Transonic Wind Tunnel by ASE (for FFA in Sweden) uses a unique injector drive which is a variation on these two methods. The CIRA HRTT Pilot Tunnel by ASE uses both injectors and fan drive in another unique drive configuration.
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