ONERA OA206 AIRFOIL (oa206-il)
ONERA OA206 AIRFOIL - ONERA/Aerospatiale OA206 rotorcraft airfoil (Constructed from patent and smoothed)
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(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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Polars for ONERA OA206 AIRFOIL (oa206-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oa206-il | 50,000 | 9 | 27.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa206-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa206-il | 100,000 | 9 | 36.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa206-il | 100,000 | 5 | 35.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa206-il | 200,000 | 9 | 46.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa206-il | 200,000 | 5 | 44.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa206-il | 500,000 | 9 | 58.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa206-il | 500,000 | 5 | 56.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa206-il | 1,000,000 | 9 | 67.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa206-il | 1,000,000 | 5 | 69.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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