Aerospace Sciences Laboratory Tour

Thomas Juliano

18 November 2009

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Overview

• Aeropace Sciences Lab (ASL) houses AAE department’s aerodynamics research

• Please do not miss way right on approach to Runway 23

• Facilities– Water tunnel– Five subsonic wind tunnels– Three supersonic wind tunnels– Hypersonic (Mach>5) wind

tunnel

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Water Tunnel• 12 in. * 12 in. test section• Approx 12 in./s top speed• Dye injection for flow

visualization• Laser Doppler Velocimeter• Lab class use

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High Contraction Tunnel

• 18 in. diameter test section

• 25 m/s (56 mph) top speed

• Lift and drag measurement for aerodynamics lab class

• Drag balance for model rockets for undergrad rocketry class

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Boeing Wind Tunnel

• 4 ft. * 6 ft. test section• 50 m/s (112 mph) top speed• 3-axis force and moment

measurement• Active for teaching and

research projects

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Mach 2.5 Supersonic Tunnel

• 2-dimensional (rectangular) nozzle with transparent side walls

• 2 in. * 2 in. test section• 30-s run time• Pressure taps, oil flow, schlieren

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Boeing/AFOSR Mach-6 Quiet Tunnel

• Ludwieg Tube• 6-10 s run time, about once per hour• p0=0.5-20 atm, T0=433 K

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Nozzle & Test Section

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Boundary Layer Transition & Quiet Flow

Boundary layer state affects surface heating, skin friction, separation, etc.

Quiet flow= low ‘noise’ level= small pressure fluctuations

Run start

Noisy flow

Intermittent noise

Turbulent burst

Quiet flow

End of run

Noise level one of several factors that contributes to boundary layer transition (geometry, Re, surface roughness, angle of attack, etc.)

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Noise Effect on HIFiRE-5α=0, T0=426 K, t=1.0 s, Smoother finish

Quiet flow, M∞=6.0, p0=980 kPa,Re=10.7*106 /m, 2009-7-7-6

Noisy flow, M∞=5.8, p0=1000 kPa, Re=11.8*106 /m, 2009-7-7-8

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Questions

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Mach 4 Supersonic Jet

• Infinite run time

• Approx 1 in. diameter jet

• Used for instrument calibration

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Purdue Quiet-Flow Ludwieg Tube

• Mach 4• Testbed for BAM6QT