ONERA OA212 AIRFOIL (oa212-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA OA212 AIRFOIL (oa212-il) Reynolds number: 200,000 Max Cl/Cd: 59.55 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa212-il-200000-n5.txt Download as CSV file: xf-oa212-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ONERA OA212 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6413 0.09252 0.08903 0.0009 0.9283 0.0283
-10.000 -0.8094 0.05267 0.04854 -0.0237 0.9174 0.0279
-9.750 -0.8634 0.03975 0.03432 -0.0216 0.9106 0.0284
-9.500 -0.8585 0.03608 0.03013 -0.0200 0.9057 0.0289
-9.250 -0.8430 0.03474 0.02865 -0.0187 0.9017 0.0292
-9.000 -0.8242 0.03335 0.02710 -0.0180 0.8974 0.0296
-8.750 -0.8044 0.03185 0.02541 -0.0175 0.8928 0.0301
-8.500 -0.7856 0.03035 0.02366 -0.0165 0.8887 0.0307
-8.250 -0.7675 0.02885 0.02188 -0.0151 0.8852 0.0315
-8.000 -0.7440 0.02723 0.01991 -0.0150 0.8806 0.0326
-7.750 -0.7206 0.02598 0.01844 -0.0145 0.8762 0.0335
-7.500 -0.6974 0.02527 0.01769 -0.0139 0.8723 0.0342
-7.250 -0.6751 0.02452 0.01683 -0.0129 0.8690 0.0351
-7.000 -0.6483 0.02356 0.01573 -0.0130 0.8643 0.0361
-6.750 -0.6224 0.02259 0.01457 -0.0128 0.8599 0.0372
-6.500 -0.5977 0.02173 0.01357 -0.0122 0.8560 0.0384
-6.250 -0.5739 0.02120 0.01302 -0.0114 0.8526 0.0396
-6.000 -0.5466 0.02063 0.01240 -0.0114 0.8483 0.0412
-5.750 -0.5190 0.01997 0.01160 -0.0114 0.8436 0.0430
-5.500 -0.4932 0.01933 0.01093 -0.0110 0.8395 0.0445
-5.250 -0.4683 0.01884 0.01042 -0.0104 0.8359 0.0461
-5.000 -0.4415 0.01837 0.00987 -0.0101 0.8320 0.0485
-4.750 -0.4130 0.01787 0.00936 -0.0103 0.8271 0.0510
-4.500 -0.3862 0.01747 0.00894 -0.0101 0.8226 0.0537
-4.250 -0.3603 0.01704 0.00843 -0.0095 0.8189 0.0568
-4.000 -0.3339 0.01665 0.00807 -0.0092 0.8152 0.0600
-3.750 -0.3046 0.01631 0.00771 -0.0095 0.8098 0.0645
-3.500 -0.2774 0.01594 0.00736 -0.0094 0.8051 0.0686
-3.250 -0.2509 0.01564 0.00702 -0.0089 0.8011 0.0738
-3.000 -0.2236 0.01529 0.00671 -0.0087 0.7954 0.0792
-2.750 -0.1960 0.01501 0.00638 -0.0085 0.7873 0.0856
-2.500 -0.1710 0.01464 0.00602 -0.0076 0.7800 0.0924
-2.250 -0.1427 0.01434 0.00572 -0.0076 0.7698 0.1004
-2.000 -0.1166 0.01405 0.00542 -0.0070 0.7626 0.1092
-1.750 -0.0875 0.01378 0.00521 -0.0072 0.7542 0.1196
-1.500 -0.0602 0.01353 0.00496 -0.0069 0.7480 0.1317
-1.250 -0.0315 0.01328 0.00477 -0.0071 0.7408 0.1476
-1.000 -0.0033 0.01300 0.00458 -0.0071 0.7332 0.1706
-0.750 0.0242 0.01267 0.00438 -0.0070 0.7263 0.2091
-0.500 0.0522 0.01215 0.00424 -0.0073 0.7176 0.3029
-0.250 0.0644 0.01031 0.00423 -0.0038 0.7110 0.7549
0.000 0.0835 0.01046 0.00462 -0.0005 0.7015 0.8729
0.250 0.1072 0.01055 0.00462 0.0011 0.6933 0.9036
0.500 0.1329 0.01064 0.00466 0.0021 0.6829 0.9235
0.750 0.1591 0.01068 0.00462 0.0032 0.6727 0.9391
1.000 0.1888 0.01070 0.00457 0.0034 0.6609 0.9530
1.250 0.2289 0.01077 0.00458 0.0015 0.6477 0.9698
1.500 0.2889 0.01093 0.00464 -0.0047 0.6307 0.9837
1.750 0.3472 0.01104 0.00464 -0.0108 0.6108 0.9933
2.000 0.3845 0.01107 0.00456 -0.0128 0.5909 0.9960
2.250 0.4166 0.01112 0.00449 -0.0138 0.5682 0.9974
2.500 0.4486 0.01121 0.00445 -0.0148 0.5422 0.9989
2.750 0.4793 0.01134 0.00444 -0.0156 0.5151 1.0000
3.000 0.5068 0.01151 0.00445 -0.0157 0.4873 1.0000
3.250 0.5340 0.01171 0.00451 -0.0159 0.4618 1.0000
3.500 0.5610 0.01192 0.00459 -0.0160 0.4403 1.0000
3.750 0.5877 0.01215 0.00471 -0.0161 0.4219 1.0000
4.000 0.6140 0.01238 0.00485 -0.0160 0.4065 1.0000
4.250 0.6399 0.01261 0.00501 -0.0160 0.3935 1.0000
4.750 0.6909 0.01308 0.00538 -0.0156 0.3709 1.0000
5.000 0.7159 0.01333 0.00559 -0.0153 0.3615 1.0000
5.250 0.7407 0.01356 0.00581 -0.0150 0.3522 1.0000
5.500 0.7651 0.01382 0.00605 -0.0146 0.3439 1.0000
5.750 0.7894 0.01405 0.00629 -0.0141 0.3353 1.0000
6.000 0.8131 0.01435 0.00655 -0.0136 0.3275 1.0000
6.250 0.8370 0.01458 0.00683 -0.0131 0.3190 1.0000
6.500 0.8601 0.01489 0.00711 -0.0126 0.3110 1.0000
6.750 0.8836 0.01513 0.00739 -0.0120 0.3014 1.0000
7.000 0.9065 0.01543 0.00769 -0.0114 0.2902 1.0000
7.250 0.9294 0.01575 0.00799 -0.0109 0.2759 1.0000
7.500 0.9527 0.01610 0.00830 -0.0105 0.2609 1.0000
7.750 0.9765 0.01643 0.00865 -0.0102 0.2468 1.0000
8.000 1.0004 0.01680 0.00903 -0.0100 0.2325 1.0000
8.250 1.0240 0.01723 0.00944 -0.0098 0.2167 1.0000
8.500 1.0469 0.01774 0.00991 -0.0096 0.1991 1.0000
8.750 1.0693 0.01830 0.01042 -0.0093 0.1785 1.0000
9.000 1.0899 0.01904 0.01105 -0.0090 0.1550 1.0000
9.250 1.1090 0.01991 0.01180 -0.0085 0.1294 1.0000
9.500 1.1262 0.02092 0.01269 -0.0079 0.1047 1.0000
9.750 1.1422 0.02200 0.01366 -0.0072 0.0850 1.0000
10.250 1.1696 0.02426 0.01583 -0.0054 0.0611 1.0000
10.500 1.1803 0.02540 0.01698 -0.0040 0.0545 1.0000
10.750 1.1917 0.02657 0.01819 -0.0028 0.0497 1.0000
11.000 1.2014 0.02791 0.01956 -0.0017 0.0461 1.0000
11.250 1.2121 0.02923 0.02095 -0.0008 0.0430 1.0000
11.500 1.2199 0.03082 0.02259 0.0001 0.0407 1.0000
11.750 1.2290 0.03235 0.02421 0.0009 0.0386 1.0000
12.000 1.2366 0.03406 0.02601 0.0016 0.0370 1.0000
12.250 1.2418 0.03603 0.02805 0.0022 0.0356 1.0000
12.500 1.2456 0.03821 0.03030 0.0026 0.0345 1.0000
12.750 1.2508 0.04032 0.03254 0.0030 0.0334 1.0000
13.000 1.2545 0.04264 0.03496 0.0032 0.0323 1.0000
13.250 1.2569 0.04517 0.03758 0.0032 0.0313 1.0000
13.500 1.2571 0.04801 0.04050 0.0030 0.0306 1.0000
13.750 1.2557 0.05112 0.04367 0.0027 0.0299 1.0000
14.000 1.2568 0.05403 0.04672 0.0024 0.0292 1.0000
14.250 1.2567 0.05717 0.04999 0.0018 0.0285 1.0000
14.500 1.2559 0.06051 0.05344 0.0011 0.0280 1.0000
14.750 1.2546 0.06400 0.05703 0.0002 0.0274 1.0000
15.000 1.2528 0.06762 0.06075 -0.0008 0.0270 1.0000
15.250 1.2507 0.07138 0.06459 -0.0019 0.0266 1.0000
15.500 1.2483 0.07520 0.06849 -0.0031 0.0262 1.0000
15.750 1.2458 0.07900 0.07233 -0.0042 0.0258 1.0000
16.000 1.2446 0.08280 0.07626 -0.0054 0.0254 1.0000
16.250 1.2430 0.08670 0.08031 -0.0068 0.0250 1.0000
16.500 1.2411 0.09068 0.08441 -0.0082 0.0245 1.0000
16.750 1.2387 0.09477 0.08862 -0.0097 0.0241 1.0000
17.000 1.2363 0.09891 0.09287 -0.0113 0.0237 1.0000
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Polar data table (+)
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