ONERA OA209 AIRFOIL (oa209-il)
ONERA OA209 AIRFOIL - ONERA/Aerospatiale OA209 rotorcraft airfoil (Constructed from patent and smoothed)
| Details | Dat file | Parser | |
|
(oa209-il) ONERA OA209 AIRFOIL ONERA/Aerospatiale OA209 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 9% at 29.3% chord. Max camber 1.6% at 17.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
ONERA OA209 AIRFOIL
57. 57.
0.0000000 0.0000000
0.0002924 0.0028551
0.0007810 0.0047471
0.0017586 0.0072243
0.0048866 0.0121590
0.0070371 0.0145844
0.0097746 0.0171549
0.0156407 0.0216181
0.0224839 0.0258454
0.0293282 0.0294448
0.0351946 0.0321729
0.0391053 0.0338387
0.0449719 0.0361378
0.0537712 0.0391946
0.0635487 0.0421315
0.0733262 0.0446694
0.0831038 0.0468743
0.0928814 0.0487973
0.1222146 0.0532210
0.1466590 0.0557137
0.1711047 0.0573865
0.1955495 0.0584144
0.2199944 0.0589332
0.2444394 0.0590590
0.2688844 0.0588899
0.2933294 0.0585127
0.3177745 0.0580034
0.3422197 0.0574183
0.3666649 0.0567851
0.3911100 0.0560989
0.4155561 0.0553337
0.4400013 0.0544535
0.4644465 0.0534314
0.4888917 0.0522542
0.5133371 0.0509200
0.5377824 0.0494348
0.5622277 0.0478067
0.5866730 0.0460385
0.6111183 0.0441303
0.6355637 0.0420791
0.6600091 0.0398820
0.6844547 0.0375358
0.7089013 0.0350436
0.7333468 0.0324094
0.7577922 0.0296382
0.7822378 0.0267311
0.8066834 0.0236749
0.8311290 0.0204437
0.8506855 0.0177115
0.8702421 0.0148404
0.8800204 0.0133593
0.8995770 0.0103632
0.9191335 0.0074690
0.9386901 0.0049059
0.9511083 0.0035814
0.9778036 0.0019806
1.0000000 0.0025150
0.0000000 0.0000000
0.0002934 -.0025969
0.0007827 -.0040758
0.0017611 -.0057866
0.0048906 -.0086200
0.0070419 -.0097936
0.0097801 -.0109121
0.0156475 -.0126099
0.0224917 -.0140076
0.0293369 -.0150912
0.0352041 -.0158681
0.0391152 -.0163313
0.0449823 -.0169601
0.0537825 -.0177994
0.0635607 -.0186385
0.0733388 -.0194185
0.0831169 -.0201646
0.0928951 -.0208907
0.1222295 -.0229909
0.1466749 -.0246691
0.1711212 -.0262593
0.1955665 -.0277175
0.2200117 -.0289996
0.2444569 -.0300718
0.2689021 -.0309240
0.2933472 -.0315792
0.3177923 -.0320834
0.3422375 -.0324905
0.3666825 -.0328357
0.3911275 -.0331239
0.4155736 -.0333301
0.4400187 -.0334213
0.4644636 -.0333685
0.4889086 -.0331596
0.5133536 -.0327928
0.5377985 -.0322740
0.5622433 -.0316132
0.5866882 -.0308134
0.6111330 -.0298756
0.6355777 -.0287947
0.6600226 -.0275679
0.6844673 -.0261931
0.7089130 -.0246733
0.7333577 -.0230135
0.7578022 -.0212177
0.7822468 -.0192799
0.8066914 -.0171821
0.8311360 -.0148962
0.8506916 -.0129154
0.8702472 -.0108045
0.8800250 -.0097146
0.8995805 -.0075468
0.9191361 -.0055509
0.9386918 -.0039291
0.9511096 -.0031806
0.9778045 -.0024304
1.0000000 -.0025080
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for ONERA OA209 AIRFOIL (oa209-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oa209-il | 50,000 | 9 | 25.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa209-il | 50,000 | 5 | 28.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa209-il | 100,000 | 9 | 36 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa209-il | 100,000 | 5 | 41.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa209-il | 200,000 | 9 | 52.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa209-il | 200,000 | 5 | 55.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa209-il | 500,000 | 9 | 75.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa209-il | 500,000 | 5 | 73.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa209-il | 1,000,000 | 9 | 90.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa209-il | 1,000,000 | 5 | 85.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||