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ONERA OA213 AIRFOIL (oa213-il)

ONERA OA213 AIRFOIL - ONERA/Aerospatiale OA213 rotorcraft airfoil (Constructed from patent and smoothed)


Airfoil oa213-il
Details Dat file Parser  
(oa213-il) ONERA OA213 AIRFOIL
ONERA/Aerospatiale OA213 rotorcraft airfoil (Constructed from patent and smoothed)
Max thickness 12.6% at 32.5% chord.
Max camber 3.3% at 25% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 ONERA OA213 AIRFOIL
       57.       57.

 0.0000000 0.0000000
 0.0002838 0.0031555
 0.0007729 0.0053479
 0.0017581 0.0082948
 0.0049279 0.0143508
 0.0074104 0.0178242
 0.0098954 0.0208388
 0.0158633 0.0272207
 0.0228298 0.0339306
 0.0297987 0.0401455
 0.0357739 0.0451065
 0.0397582 0.0482133
 0.0457366 0.0525424
 0.0547077 0.0582853
 0.0646805 0.0636948
 0.0746576 0.0682389
 0.0846384 0.0720859
 0.0946220 0.0753769
 0.1245844 0.0828279
 0.1495630 0.0870999
 0.1745473 0.0901849
 0.1995360 0.0923979
 0.2245282 0.0939440
 0.2495228 0.0949581
 0.2745197 0.0955290
 0.2995186 0.0957121
 0.3245194 0.0955371
 0.3495220 0.0950102
 0.3745262 0.0941262
 0.3995323 0.0928732
 0.4245405 0.0912473
 0.4495502 0.0892562
 0.4745617 0.0869185
 0.4995749 0.0842577
 0.5245894 0.0812926
 0.5496056 0.0780367
 0.5746233 0.0744938
 0.5996423 0.0706639
 0.6246628 0.0665432
 0.6496847 0.0621263
 0.6747080 0.0574164
 0.6997327 0.0524185
 0.7247589 0.0471506
 0.7497864 0.0416449
 0.7748147 0.0359490
 0.7998436 0.0301332
 0.8248726 0.0242963
 0.8499011 0.0185704
 0.8699231 0.0141885
 0.8899431 0.0101136
 0.8999524 0.0082396
 0.9199688 0.0049337
 0.9399813 0.0023938
 0.9599888 0.0008719
 0.9799898 0.0006629
 0.9899873 0.0011559
 1.0000000 0.0021080

 0.0000000 0.0000000
 0.0003129 -.0026655
 0.0008201 -.0041019
 0.0018283 -.0057349
 0.0050421 -.0085148
 0.0075491 -.0099074
 0.0100547 -.0110208
 0.0160650 -.0130808
 0.0230740 -.0148747
 0.0300810 -.0162867
 0.0360859 -.0172907
 0.0400888 -.0178787
 0.0460927 -.0186626
 0.0550976 -.0196666
 0.0651022 -.0206046
 0.0751060 -.0214075
 0.0851095 -.0221106
 0.0951126 -.0227375
 0.1251203 -.0243084
 0.1501255 -.0253844
 0.1751301 -.0263263
 0.2001341 -.0271692
 0.2251379 -.0279272
 0.2501408 -.0286061
 0.2751436 -.0292050
 0.3001462 -.0297190
 0.3251481 -.0301469
 0.3501498 -.0304899
 0.3751507 -.0307508
 0.4001517 -.0309388
 0.4251521 -.0310617
 0.4501522 -.0311267
 0.4751522 -.0311356
 0.5001516 -.0310836
 0.5251509 -.0309575
 0.5501497 -.0307384
 0.5751479 -.0303974
 0.6001452 -.0299023
 0.6251416 -.0292194
 0.6501369 -.0283212
 0.6751311 -.0271963
 0.7001243 -.0258443
 0.7251163 -.0242762
 0.7501072 -.0225092
 0.7750973 -.0205682
 0.8000867 -.0184811
 0.8250755 -.0162821
 0.8500641 -.0140081
 0.8700547 -.0121671
 0.8900453 -.0103371
 0.9000407 -.0094351
 0.9200320 -.0076831
 0.9400234 -.0060300
 0.9600158 -.0045190
 0.9800091 -.0031970
 0.9900061 -.0026210
 1.0000000 -.0021080
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Lednicer format dat file
Selig format dat file

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Polars for ONERA OA213 AIRFOIL (oa213-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   oa213-il50,000926.5 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   oa213-il50,000529.8 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   oa213-il100,000941.6 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   oa213-il100,000541.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   oa213-il200,000954 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   oa213-il200,000554.9 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   oa213-il500,000975.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   oa213-il500,000575.8 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   oa213-il1,000,000995.3 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oa213-il1,000,000593.7 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
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