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School of Mechanical Engineering
THE UNIVERSITY OF ADELAIDE
SA 5005
AUSTRALIA

Email: aerospace@mecheng.adelaide.edu.au

Telephone: +61 8 8303 5460
Facsimile: +61 8 8303 4367

Facilities

KC Wind Tunnel

· Low speed open return wind tunnel

· Maximum speed: 32 m/s

· Modular design, with multiple contraction sections and test sections

· Low turbulence intensity

Anechoic Wind Tunnel

Anechoic to 200 Hz
275 mm x 75 mm test jet
41 m/s top speed
Excellent low noise flow (OASPL < 50 dBA background)
Easily configurable for a wide range of industrial and research requirements.

Instrumentation

· Hot wire anemometry

· Wide variety of acoustic measurement techniques

· Laser based velocimetry: PIV, LDA

· Highly accurate automated traverse system

· Custom surface pressure, far field noise and turbulence visualisation techniques

DBD Plasma Generators

· Single Phase Plasma Generator (26 kVpp, 0-30 kHz, 110 W, 1000 g) with an on-board impedance matching unit

· Input Voltage: 15 – 40 V, max. 4 A

· Input Power < 110 W

· Maximum Output Voltage:

o ~25 kVpp at 10 kHz with plasma actuator,

o ~17 kVpp at 8 kHz with plasma actuator

· Maximum Output Power for long time ~110W

· Frequency Range: 5-30 kHz

· Waveform: sinusoidal, triangular

Shock Tube (Under Construction)

Reflected shock Facility to test autoignition properties of renewable fuel
7.2 m long, ~1 ms test time, 20 MPa pressure, 900-1800 K Temperature
Custom designed atomiser system for shock vaporisation of fuel
Easily configurable for other shock tube applications

Jet Propulsion Lab

· Design Maximum Thrust: 40 lbf (178 N)

· Approved Fuels: Jet A, A-1, B; JP-4, 5, 8; Kerosene, Diesel, Fuel Oil #1 or #2

· Exhaust Gas Temperature: 1328˚ F (720˚ C)

· Mass Flow: 1.1 lbs/s (0.5 kg/s)

· Ignition System: Air gap, high voltage capacitor discharge type hermetically sealed ignition coil and igniter plug

· Compressor Type: Single Stage Centrifugal (Radial Outflow)

· Turbine Type: Single Stage Axial Flow

· Design Maximum RPM: 87,000

· Engine Mount: Pivot bearing support allowing direct thrust to be obtained by a load cell

· Engine Compression Ratio: 3.4

· Engine Pressure Ratio: 30.0

· Specific Fuel Consumption: 1.2

· Engine Diameter: 6.8 inches (17 cm)

· Engine Length: 10.8 inches (27 cm)

Aircraft Structural Test Rig

· The port wing of a Cessna 421

· The horizontal tail structure of a Cessna 172

· 40 ECH350-5AA-11-RL30 strain gauges installed in the wing

· 20 ECH350-4BB-11-RL30 strain gauges installed in the wing

· 4 Suntronics STS – stainless steel 3k lbs load cells

· SCXI-1520 Data acquisition system

· Lab view Software