National Wind Tunnel Facility

Transcription

1 National Wind Tunnel Facility Kevin Gouder Department of Aeronautics, Imperial College

2 Key Research Challenges Turbulence the most important unsolved problem of classical physics Energy efficiency The central challenge for new fluid-based systems Fluid-structure interaction UAVs, VIV, shock waves Scalar transport Dispersion, air-sea CO 2 exchange Noise Generated by transport and energy processes High speed aerothermodynamics High M, transition, shock wave / boundary layer interaction, radiation heating

3 Need ~ 150 tunnels in UK 75 of which are in universities are research active Tunnels supported through FEC estate rate does not reflect true running costs (e.g. space charges, capital depreciation) Inefficient use of facilities EPSRC Delivery Plan: support fewer facilities in a more sustainable way Timeliness Government funding: UKAC (initial 60m); ATI 1bn over 7 years (from 2014); 60m UK Space Agency.

4 National Wind Tunnel Facility A network of 17 talent-focused facilities distributed across 7 universities Multi-sectorial research, low TRL (<3) but with aerospace focus Full range of Reynolds and Mach numbers Open access for up to 25% of time Universities are Clearly committed to wind tunnels Research intensive Prepared to demonstrate best practice Open Access

5 National Importance UK has a world-class talent base match this to world class facilities Effect of a paradigm shift for overall transformative behaviour establishing a world-leading capability Cost effectiveness Multi-sectoral appeal EPSRC portfolio: maintain fluid mechanics; grow energy efficiency/conversion. Overseas comparison (all single institution) NRC Ottawa (6 tunnels) IIT Kanpur (single low-speed tunnel) NUS/DSO Singapore (7 subsonic, 2 supersonic tunnels) National Diagnostic Facility IIT (single low speed tunnel)

6 Benefits Enhanced UK capability in experimental aerodynamics Available to all UK-based researchers Combine new capital with institutional investment Research and researchers get high visibility Creation of nodes of excellence attractors for young researchers establish a virtuous circle Economic benefits pull-through to industry spillover to other sectors

7 Added Value National Facility provides focus of international visibility for UK science Flexibility in use of facilities more efficient use of research time Institutional links to CDTs IC (fluids), Cambridge / Oxford / Loughborough (turbomachinery) Facilities provide focus for academia / industry national networks e.g. Vertical Lift Network (Agusta-Westland), DiPaRT (Airbus), ESA

8 Sustainability & Efficiency New funding model facility-specific charge-out rates addresses sustainability Coordination through dedicated web site: EPSRC / ATI engagement through CDTs, MSc scholarships Early stage engagement between host institution and investigators (at proposal draft) Ongoing resource commitment from EPSRC / ATI subject to review

9 Selected Tunnels Low speed: Cranfield, Imperial*, Southampton*, City (transition) (Re/m < ) Trans/Supersonic: Cambridge, City*, Imperial* (0.4 < M < 3.5) Hypersonic: Imperial, Oxford* (4 < M < 9) Environmental: Cranfield (ABL), Southampton* (hydroscience tank, anechoic tunnel) Aerospace: Glasgow (rotorcraft), Cranfield (icing) * New University investment ~ 65m

10 Cambridge TS1 & TS2 Operational

11 Cambridge TS1 & TS2 Operational Test section 0.12 m 0.2 m 0.6 m Mach Max flow speed m/s /m Re Total p Run Time Recharge time kpa s 20 mins Two identical facilities; Transonic/Supersonic; Open Return Blowdown Ejector system for boundary layer suction in working section Model Support: 3-component sting balance Outputs: Forces, Moments, Pressure: 3-hole and 5-hole Pitot probes; Velocity: 2-component LDA & PIV Flow-vis: Shadowgraph, Schlieren, Surface Oil Flow, Liquid Crystals, Pressure Sensitive Paint LaVision High Speed Stereoscopic PIV TSI 3 Component Laser Doppler Velocimetry TSI 3D Traverse Rig

12 City University Transonic tunnel Operational

13 City University Transonic tunnel Operational Test Section size Mach Re Max P 0 Max T 0 Turb. Intensity Run Time Recharge time 0.2 m 0.25 m 0.5 m Up to /m bar Ambient < 0.5% 30 secs. 20 mins. Transonic / Supersonic Model Support: Internal 5-component sting balance (-5-deg to +20-deg alpha range, ±180-deg roll): non-operational until testing and commissioning complete. DAQ: multiple channel, simultaneous Flow-vis: Shadowgraph, Schlieren, Surface Oil Flow Outputs: Force, Moments, Pressure High Speed Stereoscopic PIV (NWTF) 3 Component Laser Doppler Velocimetry (NWTF) Specialist Rigs: Quadrant Slotted wall and solid wall roof and floor. Floor mounted bump shock generators. Compressed air supply (under maintenance; operational January 2015).

14 City University Low Turbulence tunnel Operational

15 City University Low Turbulence tunnel Operational Test Section size & CR Mach Max Flow Speed 0.91 m 0.91 m 3m 6.75 : m/s /m /m Re Max P 0 Dynamic Pressure Ambient up to 1.24 kn/m 2 Turb. Intensity < 0.01% (up to 20 m/s) Low-speed closed return Model Support: Floor mounted Data Acquisition: 64 channel simultaneous data acquisition. Outputs: Pressure and velocity. HWA. Flow-vis: Video, tuft, surface fluorescent oil flow Available equipment/instrumentation Air blowing and suction for flow control 3 Component Laser Doppler Velocimetry (NWTF): non-oil based seeding under test. HWA incl. traversing rig plus supporting data conditioning systems Unsteady pressure instrumentation Plasma actuator support Isolated vibration rig (under development) Rotation rig with air bearings (under development)

16 Cranfield 8x6 Low Speed

17 Cranfield 8x6 Low Speed Test Section size & CR Mach Max Flow Speed Re Max P 0 Dynamic Pressure Turb. Intensity 2.4 m 1.8 m 7 : m/s /m (max) Ambient up to 1.5 kn/m 2 < 0.1% Low-speed closed return Model Support: 6-component overhead balance on 360-deg rotating roof mounted turntable. Internal 6- component balance. 6-component under-floor balance on rotating floor turntable (±25-deg yaw). Four independent wheel drag load cells. DAQ: multiple channel high speed data acquisition system. Outputs: Forces and Moments, pressure and velocity (PIV, 4-channel HWA) Flow-vis: Multiple smoke filament flow seeding, high speed video, surface oil flow Specialist Rigs Quadrant for sting mounting Air blowing and suction for flow control Rolling Road 1.2 m 2.77 m for airspeeds up to 45 m/s with two-stage boundary layer extraction system Automated active strut system for automotive models

18 Cranfield 8x4 Boundary Layer Tunnel Operational

19 Cranfield 8x4 Boundary Layer Tunnel Operational Test Section size Max Flow Speed Re Max P 0 Dynamic Pressure Turb. Intensity 2.4 m 1.2 m 15 m 16 m/s up to /m Ambient up to 162 N/m 2 < 0.1% Low-speed closed return Model Support: 6-component overhead balance. Computer controlled 3-axis traverse system. 360-deg rotating floor mounted turntable. DAQ: multiple channel high speed data acquisition system. Outputs: Forces and Moments, pressure and velocity (PIV, 4-channel HWA) Flow-vis: Multiple smoke filament flow seeding, high speed video, surface oilflow. Hydrocarbon analyser for plume dispersion studies. Specialist Rigs Interchangeable turbulence grids and surface roughness elements for atmospheric boundary layer simulation High pressure air system (blowing and suction)

20 Cranfield Icing Tunnel

21 Cranfield Icing Tunnel Test Section size Mach Flow Speed Re Max P 0 Dynamic Pressure Turb. Intensity 0.76 m 0.76 m 0.81m octagonal 0.4 m 0.4 m m/s /m /m Ambient up to 18.3 kn/m 2 < 1% Low-speed open return Flow-vis: Thermography Outputs: Forces and Moments, pressure and temperature Droplet measurement system

22 Glasgow 9x7 Tunnel (former British Aerospace/ dehavilland wind tunnel from Hatfield, Herts) Under refurbishment: fully operational April Test Section size & CR Mach Max Flow Speed Re Max P 0 Dynamic Pressure Turb. Intensity 2.66 m 2.1m 5m 5 : m/s /m (max) Ambient up to 2.94 kn/m 2 < 0.2% Low-speed closed return Flow-vis systems: Smoke, video, surface fluorescent oil flow. Outputs: Forces & moments, pressure, velocity (Stereo PIV for high resolution over large area up to 1m x 1m) Data Acquisition: 192 channel simultaneous data acquisition (16 bit) at up to 500kHz. 64 and 96 channel simultaneous data acquisition (24 bit) at up to 128kHz. Specialist Rigs: Dynamic stall Rotor rigs Sting support system 6-component balance, sting and positioning system High Speed Stereo PIV Pressure scanning system LDA system Dantec HWA High Speed Cameras Pressure Sensitive Paint 5-hole pressure probe.

23 Imperial 10 x 5 Tunnel under refurbishment operational January 2016

24 Imperial 10 x 5 Tunnel under refurbishment operational January 2016 Test Section size & CR Mach Max Flow Speed Re Max P 0 Dynamic Pressure Turb. Intensity 3.14 m 1.52 m 9 m 3.41 : (max) 45 m/s /m (max) Ambient up to 1.2 kn/m 2 < 0.15% Low-speed closed return Model Support: internal 6- component sting mounted balance (20-deg yaw range turntable). Underfloor turntable +/-20-deg yaw Rolling Road: 2.1m x 1.8m rubber/fabric belt, 45m/s, water cooled, variable profile belt suction system, twin variable speed boundary layer flow control ahead of road. Data Acquisition: National Instruments multichannel ADC, 64 channel Pressure scanning. Flow-vis: Video, surface fluorescent oil flow, smoke wand. Outputs: Forces & moments, pressure, velocity (LDV, PIV). Specialist Rigs: Model motion control system (automated pitch, manual roll and yaw) Full atmospheric boundary layer simulation capability. Automated Traverse system Tomographic PIV System Planar Laser Induced Fluorescence System 3- Component Dual Probe LDA 3D Scanning Vibrometer (1MHz) Model Force Balance/Data Acquisition/Model Motion Control DTC Intium DAQ and 2x64 Channel Pressure Scanners

25 Imperial Supersonic Tunnel Under construction University investment - operational January 2016

26 Imperial Supersonic Tunnel Under construction University investment - operational January 2016 Test Section size & CR Mach Max Flow Speed Re Turb. Intensity Run time Recharge time 0.15 m 0.15 m 2 m 20 : m/s /m (max) < 1% tbc 10 secs. 20 mins. Intermittent hybrid blow-down / suckdown arrangement Modular working section: Fully configurable test section with variable length to accommodate range of models and facilitate tests with variable boundary layer thicknesses. Control system & data acquisition: National Instruments (LabVIEW) PID tunnel controller and DAQ system. Measurement hardware: 32 channel low speed (500 Hz) pressure, 8 channel high speed (50 khz+) pressure, pressure sensitive paint, high speed schlieren, surface oil-flow and integrated seeding system for LDA and PIV. Specialist Rigs (planned) Seeding: Integrated, adjustable seeding system for solid (TiO2) & liquid droplet (Oil) flow seeding Adaptive flow control: Computer-controlled deployment of variable geometry (active) flow control devices (e.g. shock control bumps using multiple actuators using LabVIEW) Unsteadiness: Mechanism for generating unsteady pressure pulses upstream and downstream of test section (amplitude: 1-5 % p0, frequency range 10 Hz 10 khz) Gas injection: Test section module for moderate flow rate injection of various (Air, He, CO2, tbc) configurable (e.g. for scramjet fuel mixing studies)

27 Imperial Hypersonic Tunnel Operational

28 Imperial Hypersonic Tunnel Operational Test Section size & CR Mach Max Flow Speed Re P 0 T 0 Run time Recharge time 0.6 m (diameter) approx. 1 m m/s Intermittent impulsive facility Large working section: Can accommodate slender models 800+ mm in length, giving a unique (in the UK) capability for achieving high test Reynolds numbers Measurement hardware: 64 channel high speed (100 khz) DAQ with potential for further 32 channels, high speed Schlieren, surface pressure, hot films, thermographic liquid crystal, PIV & PLIF (currently in development) /m (variable) Specialist Rigs 600 bar (max, variable) 1140 K (max, variable) 20 ms 1 hr SWBLI: Numerous fundamental axis-symmetric rigs (e.g. compression ramp / cowl) for studies of SWBLI, with and without shock-induced separation Transition: e.g. Cone with roughness elements producing laminar and transitional flows, characterisation of turbulent spots Cavity flows Optical laser-based diagnostics: Toluene-based PIV / PLIF currently under development

29 Imperial High speed Facilities Available equipment/instrumentation Dantec 3-ch LDA Micromech Traverse system Dantec High Speed Camera for Schlieren Optics (high quality) Low FPS Video Camera / Lenses / Mirrors / rails / mounts / HDRecorder Camera Aerotech / Flow Dynamics High Speed Laser PIV Dantec Laser 3rd / 4th Harmonic capable Nd:YAG (to produce 266nm / 355 nm light for fluorescence measurements, e.g. molecular tagging / scalar measurements etc.) Dantec / Vision Research Low Noise Camera for fluorescence type measurements Dantec / Vision Research Intensified Camera for low photon measurements

30 Oxford T6 Free Piston Reflected Shock Tunnel Osney Thermofluids Laboratory T3 free piston driver Shortened Oxford Gun Tunnel barrel

31 Oxford T6 Free Piston Reflected Shock Tunnel Test flow size m diameter Mach Free piston, reflected shock tunnel: High total enthalpy tunnel Working gas: Air, Mars, Titan, Venus Max flow speed Re Max P 0 Max T 0 Run Time Future extension of facility to shock tube mode or expansion tunnel mode Shock tube mode allows measurements of gas kinetics/radiation post shock up to 17 km/s at 0.1 Torr air Operation in expansion tunnel mode allow for aerothermodynamics testing up to 12 km/s in air Specialist rigs: 5 10 conical nozzle with 280 mm exit diameter Mach 6, 7 & 8 contoured with mm exit diameter Boundary layer stability and transition Supersonic/Hypersonic Intake Supersonic combustion studies Free flight testing 6.5 km/s Thin Film Gauge sensitivity and frequency response calibration Pressure transducer sensitivity and frequency response calibration /m Osney Thermofluids Laboratory 75 MPa 5,000 K 1-2 ms steady T3 free piston driver Shortened Oxford Gun Tunnel barrel 18 m Recharge time 1 hr.

32 Oxford HDT High Density Tunnel Osney Thermofluids Laboratory Plug Valve Barrel

33 Oxford HDT High Density Tunnel Osney Thermofluids Laboratory Test flow size Mach Max flow speed Re Max P 0 Max T 0 Run Time Recharge time m diameter 3, 4, 5, 6, 7 contoured nozzle with mm exit diameter Mach 5-10 conical nozzle with 350 mm exit diameter 2 km/s (cold flow facility) /m 25 MPa (Heated Ludwieg) 9 MPa (LICH tunnel) 523 K (Heated Ludwieg) 1250 K (LICH tunnel) Up to 70 ms 10 mins. Heated Ludwieg / LICH tunnel Specialist rigs: Boundary Layer Stability and Transition Supersonic/Hypersonic Intake Boundary layer separation studies Freeflight testing Aerodynamic testing Thin Film Gauge sensitivity and frequency response calibration Pressure transducer sensitivity and frequency response calibration Barrel Plug Valve Driver 21 m

34 Oxford LDT Low Density Tunnel Osney Thermofluids Laboratory

35 Oxford LDT Low Density Tunnel Osney Thermofluids Laboratory Test flow size Mach Max P 0 Max T 0 Run Time Contoured Mach 6 nozzle, mm core flow Mach 5-10 conical nozzle with mm core flow kpa 600 K Continuous Rarefied Suck Down Facility (Kn < 0.3) Earth De-Orbit, Spacecraft entry Continuous cold hypersonic flow Free fly models and measure aerodynamic coefficients Magnetic suspension force balance 2-axis wake traverse of models 3-axis model traverse for re-orientation

36 Oxford: available equipment/instrumentation Osney Thermofluids Laboratory Data Acquisition Separate NI PXI chassis, 64 2 MHz each MHz aggregate LeCoy 4 channel, 5 GHz oscilliscope In-house free flight data acquisition for 6 channels up to 20 khz Probe measurements 16 x PCB-134 pressure transducer (up to 1 MHz) 24 x Kulite XTL-140M (up to 250 khz) 48 channels of thin film signal conditioning up to 1 MHz DANTEC 3 hot wire annemometer u to 400 khz Advanced thermochromic liquid crystal Optical equipment Specialised Imaging Kirana camera (up to 5 MHz) Photron Mini UX-100 camera (up to 1 MHz) LED light source up to 1 MHz Focussed Schlieren optics up to 300 mm Laser Equipment Laser Quantum 671 nm DPSS laser (LIGTS) Oxiuum low noise 532 nm DPSS laser (FLDI) Continuum Powerlite 8000 Nd:Yag laser (PLIF) Actuated traverse systems for T6 & HDT +/- 15 deg AoA. +/- 5 deg BoA

37 Southampton R.J. Mitchell tunnel Operational

38 Southampton R.J. Mitchell tunnel Operational Test section size & CR Mach Max flow speed Re Total Pressure Dynamic Pressure Turb. Intensity 3.6 m 2.5 m 10.5 m 5: m/s /m Ambient Up to < 0.2% kpa Model Support: 6-component overhead balance with various mounting options, underfloor 2- component balance and two point motorised strut for vehicle work. Data Acquisition: multichannel simultaneous data acquisition. Outputs: Forces and moments; pressure, velocity (Stereo PIV, hot wire anemometry, LaVision Tomographic PIV, LaVision Planar Laser Induced Fluorescence). Flow visualisation: Smoke, video, surface fluorescent oil flow Specialist Rigs Rolling road (up to 40m/s) with dual stage boundary layer suction. Dynamic model motion and acquisition systems have been developed previously and a new system is currently being manufactured. Rotor rigs have been developed and used in this tunnel as well as propeller/rudder rigs.

39 Southampton Anechoic tunnel Under Construction; University Investment. Operational March 2015 Test section size & CR Anechoic Chamber size Mach Max flow speed Re (max) Total Pressure Dynamic Pressure Turbulence Intensity 1.0 m 0.75 m 8: m 5.5 m 4.75 m m/s /m Ambient Up to n/k Anechoic Wind Tunnel Acoustic: Farfield microphones and phased microphone array Flow visualisation: Video, surface fluorescent oil flow. Aerodynamic loads: Capability to measure surface pressures and loads Laser Measurements: Capability to perform particle image velocimetry measurements Equipment & Instrumentation: Cross-wire HWA Chiller and heat-exhanger for wind tunnel Model support and Traverse System DAQ Microphone array, kulites, arcs, mics, preamps, holders and leads Specialist Rigs: Arc of farfield microphones that can be traversed to obtain comprehensive directivity information Simultaneous microphone array and laser diagnostics It will be a unique facility within the UK that is able to conduct airframe noise and loads tests, as well as some specialist propulsive (engine) research

40 Southampton Hydroscience Tank Under Construction; University Investment. Operational March Test section size Max Carriage Speed Re (max) Dynamic Pressure Runtime 140 m long x 6 m wide x 3.5 m deep with 0.5 m free board m/s /m Up to 50 kn/m 2 Varies with carriage speed Towing and Wave Tank Model Support: Variety of tow posts, either fixed pitch/heave/roll. Forced motions via HPMM or VPMM for surge, sway/yaw or heave/pitch. Multi component dynamometer frame as necessary for resistance/thrust, sideforce, vertical force and moments. Data Acquisition: Experiment specific multichannel minimum 250 Hz up to 250 khz for acoustic measurements. Synchronised force/moments with video motion capture/visualisation. Also 9 degree offreedom IMU. Surface pressures. PIV/LDV. Flow visualisation: Multi camera HD Video, surface die, tufts. Field Measurement: Underwater stereo PIV, 2-comp. underwater LDV, Pitot-static traverse. Specialist Rigs: Passive beach at end of tank with Active wave makers (6-10) across other end that can generate irregular sea states with max. amplitude of 0.5m for wide range of model scale wave frequencies. Deployable side beach to damp waves rapidly between runs Wave makers Modular instrumentation stations and fixings to walls/floor of tank Low speed manned and high speed unmanned carriage Mid length divider to provide two test spaces Automated carriage and test process Control room with multiple video feeds and live data streaming

41 Key Performance Indicators 1. The Number potential Users that have been in contact with the NWTF and the number of Users that actually made use of any of the facilities of the NWTF. 2. The Uptime (or Downtime) of the NWTF facilities (wind tunnels) and accompanying equipment within the period. 3. Number of extended Outages (> 3 weeks) 4. The usage of each facility expressed as i) a percentage of the whole year and ii) a percentage of the Uptime. 5. Number of User Complaints received during the period. This should be expressed as a percentage of the Total Number of User Approvals made within the period. 6. Publications using data obtained using a facility of the NWTF and its equipment.

42 Service Level Agreement The time from receipt of the Technical Annex by the NWTF Project Manager to informing a User of receipt will be less than 3 days The time from receipt of the Technical Annex and a response from the indicated facility's managers will be less than 14 days The Facility will be operational and available for use for 70% of maximum possible operational time The NWTF will respond to all User enquiries clearly and quickly in line with the following timescales: To or fax enquires within 3 (three) working days To telephone enquiries within 2 (two) working days The NWTF will respond to user complaints within 10 (ten) working days The NWTF will treat all proposals equally and fairly The NWTF will treat all Users equally and fairly The NWTF will uphold high standards of integrity in all operations and in contact with Users

43 Management & Access Management Board: investigators: Prof Jonathan Morrison (Chair) Prof Chris Atkin Prof Holger Babinsky Prof Bharathram Ganapathisubramani Prof Kevin Garry Dr Richard Green Prof Peter Ireland / Dr Matt McGilvray + Project manager Dr Kevin Gouder + EPSRC (ex officio) Project Manager: day-to-day (tunnel time allocations) liaises with local tunnel managers Advisory Board: Mr Adrian Gaylard (Jaguar LandRover) (Chair) Prof Henrik Alfredsson (KTH Royal Institute of Technology) Dr Nicolas Guernion (EPSRC) Dr Richard Markiewicz (DSTL) Prof Jim McGuirk (Loughborough University) Mr Frank Ogilvie (ATI Aerospace Technology Institute) Mr Mick Simmons (Airbus) Prof Alexander Smits (Princeton University) Dr Johan Steelant (ESA)

44 Management & Access Balance uptake with economic sustainability External vs internal users Variable research income Research vs. commercial income Affiliate institutions provide Scheduling flexibility Direct links with industry

45 Access Researchers interested in making use of one of the facilities to open a dialogue with NWTF personnel at an early stage of the proposal formulation. This ensures the best facility and equipment are identified and facility time required pre-booked. A Technical Annex (downloaded from the website) completed and sent to admin@nwtf.ac.uk The proposal is not assessed this is the responsibility of the funding agency. Meetings between researcher and facility held to discuss details and a mutual decision is made on whether to go ahead. IP identified and recorded at an early stage. Non-disclosure agreement signed between researcher and NWTF.

46 Progress Update Jan 1 st 2014 Jan 9 th 2014 March 17 th 2014 July 23 rd 2014 Feb 3 rd 2015 Grant start Inaugural Management Board meeting Project Manager start Most of facilities received equipment, commissioned it, and are in the process of agreed refurbishment ToR for Management and Advisory Boards Website launch Service Level Agreement Technical Annex Facility visits 1 st Advisory Board Meeting Imperial College London

47 Progress Update Jan 1 st 2014 Jan 1 st 2015 Jan 1 st 2016 Jan 1 st 2017 Jan 1 st 2018 AB Meeting AB Meeting AB Meeting AB Meeting Mid-term review: 2.5 years Balance of Facilities Balance of Usage