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ONERA OA206 AIRFOIL (oa206-il)

ONERA OA206 AIRFOIL - ONERA/Aerospatiale OA206 rotorcraft airfoil (Constructed from patent and smoothed)


Airfoil oa206-il
Details Dat file Parser  
(oa206-il) ONERA OA206 AIRFOIL
ONERA/Aerospatiale OA206 rotorcraft airfoil (Constructed from patent and smoothed)
Max thickness 6% at 31.8% chord.
Max camber 0.8% at 19.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 ONERA OA206 AIRFOIL
       57.       57.

 0.0000000 0.0000000
 0.0002931 0.0017830
 0.0007833 0.0028869
 0.0017614 0.0042928
 0.0048918 0.0071184
 0.0070430 0.0085542
 0.0097812 0.0101149
 0.0156494 0.0128942
 0.0224938 0.0155764
 0.0293390 0.0178837
 0.0352063 0.0196400
 0.0391173 0.0207156
 0.0449845 0.0222029
 0.0537858 0.0241829
 0.0635641 0.0260808
 0.0733421 0.0277147
 0.0831203 0.0291326
 0.0928984 0.0303725
 0.1222337 0.0332842
 0.1466790 0.0350184
 0.1711251 0.0362787
 0.1955702 0.0371429
 0.2200163 0.0376601
 0.2444613 0.0378783
 0.2689063 0.0378496
 0.2933513 0.0376368
 0.3177963 0.0373091
 0.3422413 0.0369193
 0.3666872 0.0364955
 0.3911321 0.0360318
 0.4155781 0.0355090
 0.4400231 0.0349043
 0.4644679 0.0341974
 0.4889128 0.0333836
 0.5133578 0.0324589
 0.5378026 0.0314272
 0.5622464 0.0302964
 0.5866914 0.0290697
 0.6111363 0.0277489
 0.6355810 0.0263351
 0.6600258 0.0248304
 0.6844697 0.0232356
 0.7089157 0.0215568
 0.7333604 0.0198021
 0.7578040 0.0179743
 0.7822489 0.0160736
 0.8066926 0.0140898
 0.8311374 0.0120120
 0.8506932 0.0102788
 0.8702480 0.0084906
 0.8800259 0.0075865
 0.8995807 0.0058093
 0.9191365 0.0041681
 0.9386923 0.0027949
 0.9511103 0.0021295
 0.9778042 0.0014345
 1.0000000 0.0017790

 0.0000000 0.0000000
 0.0002927 -.0018150
 0.0007826 -.0029451
 0.0017605 -.0043192
 0.0048903 -.0066775
 0.0070412 -.0076498
 0.0097790 -.0085591
 0.0156468 -.0099008
 0.0224907 -.0109675
 0.0293356 -.0117773
 0.0352026 -.0123530
 0.0391135 -.0126944
 0.0449805 -.0131591
 0.0537815 -.0137811
 0.0635594 -.0144062
 0.0733373 -.0149883
 0.0831153 -.0155414
 0.0928931 -.0160685
 0.1222281 -.0175038
 0.1466729 -.0185446
 0.1711188 -.0194553
 0.1955637 -.0202471
 0.2200097 -.0209338
 0.2444546 -.0215226
 0.2688995 -.0220204
 0.2933445 -.0224311
 0.3177895 -.0227629
 0.3422345 -.0230327
 0.3666804 -.0232574
 0.3911254 -.0234422
 0.4155714 -.0235779
 0.4400164 -.0236467
 0.4644614 -.0236315
 0.4889064 -.0235222
 0.5133515 -.0233150
 0.5377965 -.0230128
 0.5622405 -.0226175
 0.5866855 -.0221303
 0.6111307 -.0215490
 0.6355757 -.0208698
 0.6600208 -.0200886
 0.6844649 -.0192013
 0.7089111 -.0182081
 0.7333562 -.0171068
 0.7578002 -.0158956
 0.7822454 -.0145634
 0.8066896 -.0130921
 0.8311347 -.0114609
 0.8506908 -.0100291
 0.8702461 -.0084883
 0.8800242 -.0076864
 0.8995793 -.0060626
 0.9191355 -.0045049
 0.9386917 -.0031391
 0.9511098 -.0024355
 0.9778039 -.0015335
 1.0000000 -.0015690
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Lednicer format dat file
Selig format dat file

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Polars for ONERA OA206 AIRFOIL (oa206-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   oa206-il50,000927.3 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   oa206-il50,000527.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   oa206-il100,000936.4 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oa206-il100,000535.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   oa206-il200,000946.1 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   oa206-il200,000544.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   oa206-il500,000958.6 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   oa206-il500,000556.3 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   oa206-il1,000,000967.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oa206-il1,000,000569.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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