ONERA OA212 AIRFOIL (oa212-il)
ONERA OA212 AIRFOIL - ONERA/Aerospatiale OA212 rotorcraft airfoil (Constructed from patent and smoothed)
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(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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Polars for ONERA OA212 AIRFOIL (oa212-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oa212-il | 50,000 | 9 | 26.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 50,000 | 5 | 31.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 100,000 | 9 | 44.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 100,000 | 5 | 45.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 200,000 | 9 | 60.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 200,000 | 5 | 59.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 500,000 | 9 | 82.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 500,000 | 5 | 76.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 1,000,000 | 9 | 96.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 1,000,000 | 5 | 87 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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