ONERA OA213 AIRFOIL (oa213-il)
ONERA OA213 AIRFOIL - ONERA/Aerospatiale OA213 rotorcraft airfoil (Constructed from patent and smoothed)
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(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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Polars for ONERA OA213 AIRFOIL (oa213-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oa213-il | 50,000 | 9 | 26.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 50,000 | 5 | 29.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 100,000 | 9 | 41.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 100,000 | 5 | 41.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 200,000 | 9 | 54 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 200,000 | 5 | 54.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 500,000 | 9 | 75.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 500,000 | 5 | 75.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 1,000,000 | 9 | 95.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 1,000,000 | 5 | 93.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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