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ONERA OA212 AIRFOIL (oa212-il)

ONERA OA212 AIRFOIL - ONERA/Aerospatiale OA212 rotorcraft airfoil (Constructed from patent and smoothed)


Airfoil oa212-il
Details Dat file Parser  
(oa212-il) ONERA OA212 AIRFOIL
ONERA/Aerospatiale OA212 rotorcraft airfoil (Constructed from patent and smoothed)
Max thickness 12% at 31.8% chord.
Max camber 2.3% at 31.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 ONERA OA212 AIRFOIL
       57.       57.

 0.0000000 0.0000000
 0.0002938 0.0035259
 0.0007843 0.0056748
 0.0017629 0.0083576
 0.0048943 0.0135608
 0.0070459 0.0161303
 0.0097846 0.0188886
 0.0156537 0.0237732
 0.0224989 0.0285165
 0.0293449 0.0326639
 0.0352127 0.0358904
 0.0391241 0.0379045
 0.0449919 0.0407501
 0.0537938 0.0446780
 0.0635728 0.0486366
 0.0733517 0.0522392
 0.0831304 0.0555338
 0.0929092 0.0585534
 0.1222460 0.0661882
 0.1466922 0.0711563
 0.1711392 0.0750505
 0.1955849 0.0780055
 0.2200314 0.0801436
 0.2444768 0.0815846
 0.2689220 0.0824558
 0.2933670 0.0828809
 0.3178121 0.0829609
 0.3422570 0.0827660
 0.3667029 0.0823351
 0.3911477 0.0816821
 0.4155936 0.0807993
 0.4400384 0.0796614
 0.4644830 0.0782394
 0.4889276 0.0765126
 0.5133721 0.0744706
 0.5378165 0.0721217
 0.5622599 0.0694808
 0.5867041 0.0665609
 0.6111485 0.0633739
 0.6355926 0.0599251
 0.6600366 0.0562232
 0.6844798 0.0522823
 0.7089249 0.0481214
 0.7333687 0.0437645
 0.7578115 0.0392326
 0.7822554 0.0345337
 0.8066982 0.0296718
 0.8311419 0.0246508
 0.8506969 0.0205391
 0.8702510 0.0163934
 0.8800285 0.0143380
 0.8995826 0.0103823
 0.9191377 0.0068406
 0.9386930 0.0040058
 0.9511107 0.0027238
 0.9778045 0.0017804
 1.0000000 0.0033190

 0.0000000 0.0000000
 0.0002920 -.0036491
 0.0007815 -.0059592
 0.0017588 -.0088294
 0.0048876 -.0139952
 0.0070381 -.0162487
 0.0097755 -.0184354
 0.0156426 -.0217968
 0.0224860 -.0245514
 0.0293306 -.0266291
 0.0351972 -.0280605
 0.0391080 -.0288785
 0.0449747 -.0299349
 0.0537755 -.0312120
 0.0635532 -.0322994
 0.0733309 -.0331307
 0.0831088 -.0337791
 0.0928867 -.0342935
 0.1222214 -.0353436
 0.1466663 -.0359065
 0.1711122 -.0363294
 0.1955571 -.0366613
 0.2200030 -.0369142
 0.2444480 -.0370821
 0.2688931 -.0371610
 0.2933381 -.0371670
 0.3177830 -.0371388
 0.3422281 -.0371228
 0.3666741 -.0371517
 0.3911190 -.0372266
 0.4155650 -.0373124
 0.4400100 -.0373654
 0.4644550 -.0373473
 0.4889000 -.0372382
 0.5133451 -.0370281
 0.5377902 -.0367170
 0.5622342 -.0363080
 0.5866794 -.0357999
 0.6111245 -.0351818
 0.6355697 -.0344437
 0.6600149 -.0335717
 0.6844593 -.0325535
 0.7089056 -.0313805
 0.7333509 -.0300404
 0.7577952 -.0285063
 0.7822406 -.0267383
 0.8066850 -.0246742
 0.8311306 -.0222471
 0.8506871 -.0200018
 0.8702428 -.0174786
 0.8800212 -.0161239
 0.8995768 -.0133047
 0.9191335 -.0104824
 0.9386901 -.0078632
 0.9511085 -.0064092
 0.9778031 -.0041316
 1.0000000 -.0033810
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Lednicer format dat file
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Polars for ONERA OA212 AIRFOIL (oa212-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   oa212-il50,000926.2 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oa212-il50,000531.6 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   oa212-il100,000944.3 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oa212-il100,000545.6 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   oa212-il200,000960.4 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   oa212-il200,000559.5 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   oa212-il500,000982.2 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   oa212-il500,000576.3 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   oa212-il1,000,000996.6 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   oa212-il1,000,000587 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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