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BOEING-VERTOL VR-1 AIRFOIL (vr1-il)

BOEING-VERTOL VR-1 AIRFOIL - Boeing-Vertol VR-1 rotorcraft airfoil


Airfoil vr1-il
Details Dat file Parser  
(vr1-il) BOEING-VERTOL VR-1 AIRFOIL
Boeing-Vertol VR-1 rotorcraft airfoil
Max thickness 11% at 35.3% chord.
Max camber 1.5% at 43.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 BOEING-VERTOL VR-1 AIRFOIL
25.        25.
 
 0.         0.
  .00559     .01673
  .01850     .02600
  .02943     .03066
  .03729     .03336
  .05173     .03747
  .08439     .04440
  .11326     .04935
  .15252     .05505
  .19215     .05957
  .23220     .06329
  .31250     .06812
  .35269     .06934
  .43331     .06947
  .51428     .06632
  .55468     .06349
  .59474     .05991
  .63471     .05567
  .67453     .05087
  .75387     .03984
  .83291     .02748
  .91183     .01451
  .94622     .00881
  .98650     .00223
 1.0         .0000
 
 0.         0.
  .00559    -.01001
  .01850    -.01570
  .02943    -.01910
  .03729    -.02120
  .05173    -.02430
  .08439    -.02965
  .11326    -.03270
  .15252    -.03580
  .19215    -.03795
  .23220    -.03985
  .31250    -.04045
  .35269    -.04040
  .43331    -.03880
  .51428    -.03580
  .55468    -.03395
  .59474    -.03180
  .63471    -.02920
  .67453    -.02650
  .75387    -.02050
  .83291    -.01382
  .91183    -.00695
  .94622    -.00395
  .98650    -.00083
 1.0         .0000
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Lednicer format dat file
Selig format dat file

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Polars for BOEING-VERTOL VR-1 AIRFOIL (vr1-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   vr1-il50,000930.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   vr1-il50,000530 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   vr1-il100,000946.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   vr1-il100,000544.1 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   vr1-il200,000963.5 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   vr1-il200,000553.6 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   vr1-il500,000972.8 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   vr1-il500,000561.1 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   vr1-il1,000,000977.8 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   vr1-il1,000,000575.6 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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