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Aerospace Sciences Laboratory Tour

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

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  1. 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. 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.)

  10. 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

  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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