aerospace sciences laboratory tour thomas juliano 18 november 2009
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Aerospace Sciences Laboratory Tour
Thomas Juliano
18 November 2009
2
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
3
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
4
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
5
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
6
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
7
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
8
Nozzle & Test Section
9
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.)
10
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
11
Questions
12
Mach 4 Supersonic Jet
• Infinite run time
• Approx 1 in. diameter jet
• Used for instrument calibration
13
Purdue Quiet-Flow Ludwieg Tube
• Mach 4• Testbed for BAM6QT
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