Facility  Improvement    &   Data  Op=miza=on  (FIDO)     Efforts  at  the  NASA  NTF       Eric  L.  Walker  &  Roman  Paryz       Presented  at  the AIAA SciTech Conference Aerospace Sciences Meeting (ASM) 5  -­‐  9  Jan  uary  2015   Kissimmee, FL   Subject  Category:  Test  FaciliBes,  Transonic  Wind  Tunnel   Key  Words:  ModificaBons  /  Upgrades         APPROVED  FOR  PUBLIC  RELEASE   NASA  Langley  Research  Center What  is  FIDO   •  A  concentrated,  mul=-­‐year  effort  to  improve  NTF’s  overall  capabili=es   •  An  ins=tu=onaliza=on  of  lessons  learned  from  the  STARBUKS  project   (Subsonic  Transonic  Applied  Refinements  By  Using  Key  Strategies)   •  This  mul=-­‐million  dollar  effort  is  making  improvements  to  our   –  Accuracy  and  Valida=on     •  Improved  repeatability  /  data  quality  for  results  that  can  be  trusted   –  Produc=vity   •  CompleBng  required  tesBng  in  a  Bmely  manner   –  Reliability   •  Keep  the  facility  operaBonal  without  interrupBon   NASA  Langley  Research  Center   2 STARBUKS  Summary   Accuracy  &  Valida=on   þ  Data  Acquisi=on  System  (Test  SLATE)   þ  Mach  Measurement  System    üC  heck  Std   Test  214   þ  Facility  Automa=on  System   þ  Cooling  Coil  Trailing  Edge  Fairings   þ  Fixed  Fairing  Extension    ü   þ  Alt.  Probes  Loca=ons  (RTD  on  Cooling  Coil)   þ  Test  Sec=on  Visibility   þ  Balance  Calibra=ons   þ     Completed   Produc=vity   þ  Cryogenic  Ac=ve  Damper   þ  Balance  Limit  Alarm  (BLAMS)  Upgrade   þ  Inlet  Guide  Vane  (IGV)  ΔT  Mi=ga=on   þ  Con=nuous  Pitch      ü  Flow   Calibra=on   Test  217   Reliability   þ  High  Pressure  Air  Reducing  Sta=on   CRM  Data  Flow  Quality   þ  Drive  Coupling    ü   Test  218   þ  IGV  Hydraulic  Pipe  Repair   NASA  Langley  Research  Center   See  Paryz  AIAA  2014-­‐1481   CRM  –  Common  Research  Model   3 FIDO  Improvements  Roadmap   Accuracy  &  Valida=on    üC  heck  Std   ¨  Tunnel  configura=on  selec=on   Test  219   ¨  Mach  stability  ±0.0005    ü   þ  Condi=onal  sampling  (off-­‐line)   þ  Validate  RTD  array  on  cooling  coil   Produc=vity   þ     Completed   ¨  Mach  control  methodology   ¨  2nd  throat  actua=on   ¨  Condi=onal  sampling  (on-­‐line,  real-­‐=me)   ¨  Increase  access  housing  hea=ng   ¨  Op=mized  nitrogen  injec=on   Calibra=on   þ  Con=nuous  sweep   Extension   Test  220   Turbulence   Survey  Rake   Test  216B   Reliability   ¨  Liquid  nitrogen  pump  health  monitoring   CRM   Test  221   ¨  Minimize  nitrogen  system  hammering   NASA  Langley  Research  Center   CRM  –  Common  Research  Model   4 FIDO  Projects  and  Tests   •  5  Major  Projects   •  5  Experimental  Entries   –  Test  Sec=on  Movables  (2nd  Throat)     –  Test  219  Check  standard   §  Tunnel  configuraBon  selecBon   [Pathfinder]     §  Mach  control  methodology   §  Mach  control  methodology   §  2nd  throat  actuaBon   §  ConBnuous  sweep  opBmizaBon   –  Condi=onal  Sampling   –  Test  216A&B  Flow  survey  rake     §  Off-­‐line  [Complete]   §  Validate  RTD  array   §  On-­‐line  real-­‐Bme   §  Verify  turbulence  reducBon  from   –  Increasing  Access  Housing  Hea=ng   STARBUKS  [Deferred  due  to  budget]     –  Propor=onal  Liquid  Nitrogen  (LN2)   –  Test  220  Calibra=on  extension   Injec=on   §  Mach  control  methodology   §  OpBmized  nitrogen  injecBon   –  Test  221  CRM  valida=on   §  Minimize  nitrogen  system  hammering   §  ValidaBon  of  combined  system   –  LN2  Pump  Health  Monitoring   upgrades       NASA  Langley  Research  Center   5 Na=onal  Transonic  Facility  –  NTF   30  Years  of  High  Reynolds  Number  RDT&E   The  Highest  Reynolds  Number  Transonic  Facility  Opera=ng  in  Air   The  Highest  Reynolds  Number  Transonic  Facility  Opera=ng  Cryogenically   Test  SecBon   8.2  x  8.2  x  25  Feet  (  2.5  x  2.5  x  7.6  meters)   Pressure   14.7  to  133  psia;  1  to  9.0  atm.;  1.01  to  9.1  bar   Air  Opera=ons   N  Opera=ons   2 Mach  No.   0.2  to  1.05   0.2  to  1.20   Reynolds  No.  Max   20x106  /  h  (65x106  /  m)   145x106  /  h  (475x106  /  m)   Temperature   90°  to  150°F  (32°  to  65°C)   -­‐50°  to  -­‐250°F  (-­‐45°  to  -­‐157°C)   150   140   130   )   t F120   /   s  110   n o Milli10900     ( er   80   b m 70   u N 60   s   d 50   ol n 40   y Re 30   20   10   0   0   0.1   0.2   0.3   0.4   0.5   0.6   0.7   0.8   0.9   1.0   1.1   1.2   1.3   Mach  Number   NASA  Langley  Research  Center   6 Test  Sec=on  Movables  (2nd  Throat)   Accuracy  &  Valida=on,  Produc=vity   •  Improve  Mach  stability  (physical)   –  Target  ±0.0005  Mach  number  for  transonic   condiBons   –  Part  of  original  NTF  design  for  “superior  Mach   control”   •  Project  components   –  Develop  a  robust  instrumentaBon  package  to   determine  wall  posiBon   –  Develop  a  remote  wedge  system  for  the  fixed   faring  to  minimize  support  system  induced   dynamics   •  Planned  to  be  opera=onal  in  Summer  2015   •  Requires  calibra=on  extension   NASA  Langley  Research  Center   See  Chan  AIAA  2015-­‐####  and  Jones  AIAA  2015-­‐####     7 Condi=onal  Sampling   Accuracy  &  Valida=on,  Produc=vity   •  Improve  data  quality   –  Reject  data  samples  that  do  not   meet  requirements   C ±0.0001   Condi=onal  Sample   Condi=onal  Sample   D Avg  1st  2  Sec   1st  2  Sec   1st  Valid  2  Sec  (of  12)   •  Off-­‐line:  available   –  Performance  penalty  due  to   longer  data  samples  required   –  Need  ~2  seconds  of  valid  data   –  May  need  to  acquire  10-­‐12  sec   •  On-­‐line:  in  development   –  Stop  acquiring  data  when   samples  meet  specified  criteria   –  Alleviates  most  of  performance   penalty     NASA  Langley  Research  Center   M±0.0005   8 Increasing  Access  Housing  Hea=ng   Produc=vity   •  Target   –  50%  reducBon  in  model   access  Bme   •  Current  system   –  20  kW  convecBon  heater   –  2  torch  heaters  (convecBon)   –  2  IR  lamps  for  sBng  base   •  Approach   –  Replace  torch  heaters  with   medium-­‐wave  (mw)  IR   heaters   –  4  mwIR  heaters  with   independent  control  using  an   4  opBcal  pyrometers  for   surface  temperature   measurement   –  New  arBculaBng  arm   structure     NASA  Langley  Research  Center   9 Propor=onal  Liquid  Nitrogen  (LN )  Injec=on   2 Accuracy  &  Valida=on,  Reliability   •  Current  system   –  336  injecBon  nozzles  controlled  by   12  binary  (buqerfly)  valves   –  8  programmed  injecBon  paqerns   •  Proposed  changes   –  Replace  binary  valves  with   proporBonal  (ball)  valves   –  Update  the  automaBon  hardware   –  Revise  control  system   –  Incorporate  RTD  array  for  fine   temperature  control   •  Proposed  benefits   –  OpBmized  LN  injecBon   2 –  Minimized  LN  system  dynamics   2 –  Improved  reliability  of  LN  system   2 •  Planned  to  be  opera=onal  in   Summer  2015   NASA  Langley  Research  Center   10