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Aerospace Sciences Laboratory Tour. Thomas Juliano 18 November 2009. 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

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aerospace sciences laboratory tour

Aerospace Sciences Laboratory Tour

Thomas Juliano

18 November 2009

overview
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
water tunnel
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
high contraction tunnel
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
boeing wind tunnel
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
mach 2 5 supersonic tunnel
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
boeing afosr mach 6 quiet tunnel
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
boundary layer transition quiet flow
Run start

Intermittent noise

Turbulent burst

Noisy flow

Quiet flow

End of run

Boundary Layer Transition & Quiet Flow

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

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

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

noise effect on hifire 5 0 t 0 426 k t 1 0 s smoother finish
Noise Effect on HIFiRE-5α=0, T0=426 K, t=1.0 s, Smoother finish

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

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

mach 4 supersonic jet
Mach 4 Supersonic Jet
  • Infinite run time
  • Approx 1 in. diameter jet
  • Used for instrument calibration
purdue quiet flow ludwieg tube
Purdue Quiet-Flow Ludwieg Tube
  • Mach 4
  • Testbed for BAM6QT
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