ONERA OA212 AIRFOIL (oa212-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA OA212 AIRFOIL (oa212-il) Reynolds number: 200,000 Max Cl/Cd: 60.36 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oa212-il-200000.txt Download as CSV file: xf-oa212-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3646 0.10157 0.09838 -0.0185 1.0000 0.0725
-9.750 -0.4063 0.09339 0.09023 -0.0291 1.0000 0.0745
-9.500 -0.4010 0.08810 0.08495 -0.0296 1.0000 0.0753
-9.250 -0.3779 0.08610 0.08295 -0.0276 1.0000 0.0764
-9.000 -0.3685 0.08283 0.07968 -0.0283 1.0000 0.0776
-8.750 -0.5521 0.07817 0.07471 -0.0372 1.0000 0.0751
-8.500 -0.5247 0.07661 0.07329 -0.0347 1.0000 0.0760
-8.250 -0.5083 0.07436 0.07103 -0.0350 0.9922 0.0773
-8.000 -0.4955 0.07052 0.06714 -0.0383 0.9849 0.0790
-7.750 -0.5703 0.04490 0.03987 -0.0452 0.9685 0.0573
-7.500 -0.5537 0.04218 0.03707 -0.0447 0.9618 0.0562
-7.250 -0.5429 0.03873 0.03335 -0.0434 0.9544 0.0555
-7.000 -0.5328 0.03489 0.02901 -0.0418 0.9471 0.0555
-6.750 -0.5213 0.03191 0.02546 -0.0394 0.9404 0.0562
-6.500 -0.5022 0.02945 0.02244 -0.0383 0.9338 0.0569
-6.250 -0.4849 0.02744 0.02024 -0.0367 0.9282 0.0579
-6.000 -0.4596 0.02631 0.01906 -0.0366 0.9218 0.0592
-5.750 -0.4382 0.02563 0.01828 -0.0353 0.9162 0.0611
-5.500 -0.4129 0.02460 0.01698 -0.0349 0.9106 0.0637
-5.250 -0.3890 0.02338 0.01549 -0.0340 0.9048 0.0659
-5.000 -0.3679 0.02267 0.01480 -0.0325 0.9000 0.0680
-4.750 -0.3388 0.02201 0.01408 -0.0329 0.8939 0.0712
-4.500 -0.3143 0.02158 0.01344 -0.0319 0.8886 0.0747
-4.250 -0.2921 0.02075 0.01269 -0.0307 0.8840 0.0783
-4.000 -0.2627 0.02025 0.01215 -0.0311 0.8777 0.0830
-3.750 -0.2386 0.01960 0.01147 -0.0301 0.8725 0.0881
-3.500 -0.2170 0.01927 0.01117 -0.0284 0.8682 0.0935
-3.250 -0.1886 0.01865 0.01052 -0.0286 0.8600 0.1004
-3.000 -0.1692 0.01821 0.01011 -0.0261 0.8534 0.1073
-2.750 -0.1451 0.01761 0.00953 -0.0250 0.8443 0.1157
-2.500 -0.1241 0.01716 0.00908 -0.0229 0.8372 0.1248
-2.250 -0.1008 0.01663 0.00861 -0.0217 0.8311 0.1354
-2.000 -0.0740 0.01618 0.00822 -0.0213 0.8239 0.1486
-1.750 -0.0511 0.01573 0.00780 -0.0198 0.8191 0.1637
-1.500 -0.0258 0.01524 0.00746 -0.0192 0.8131 0.1853
-1.250 0.0003 0.01466 0.00712 -0.0188 0.8059 0.2267
-1.000 0.0161 0.01275 0.00664 -0.0168 0.8011 0.5444
-0.750 0.0186 0.01249 0.00752 -0.0084 0.7944 0.8971
-0.500 0.0391 0.01271 0.00768 -0.0049 0.7873 0.9388
-0.250 0.0900 0.01277 0.00760 -0.0075 0.7828 0.9675
0.000 0.1708 0.01286 0.00757 -0.0174 0.7756 0.9869
0.250 0.2315 0.01270 0.00731 -0.0236 0.7680 1.0000
0.500 0.2550 0.01251 0.00703 -0.0225 0.7597 1.0000
0.750 0.2794 0.01233 0.00678 -0.0217 0.7503 1.0000
1.000 0.3041 0.01217 0.00655 -0.0210 0.7408 1.0000
1.250 0.3279 0.01198 0.00628 -0.0199 0.7307 1.0000
1.500 0.3539 0.01185 0.00610 -0.0195 0.7186 1.0000
1.750 0.3785 0.01170 0.00587 -0.0186 0.7074 1.0000
2.000 0.4036 0.01156 0.00566 -0.0179 0.6944 1.0000
2.250 0.4298 0.01145 0.00551 -0.0175 0.6787 1.0000
2.500 0.4558 0.01137 0.00536 -0.0170 0.6617 1.0000
2.750 0.4815 0.01130 0.00521 -0.0164 0.6428 1.0000
3.000 0.5079 0.01128 0.00511 -0.0161 0.6200 1.0000
3.250 0.5343 0.01131 0.00502 -0.0158 0.5936 1.0000
3.500 0.5609 0.01140 0.00498 -0.0155 0.5646 1.0000
3.750 0.5875 0.01158 0.00498 -0.0154 0.5350 1.0000
4.000 0.6141 0.01181 0.00506 -0.0153 0.5069 1.0000
4.250 0.6404 0.01210 0.00518 -0.0153 0.4838 1.0000
4.500 0.6665 0.01239 0.00537 -0.0152 0.4637 1.0000
4.750 0.6922 0.01271 0.00557 -0.0150 0.4471 1.0000
5.000 0.7173 0.01306 0.00579 -0.0147 0.4329 1.0000
5.250 0.7424 0.01336 0.00606 -0.0144 0.4197 1.0000
5.500 0.7673 0.01368 0.00636 -0.0141 0.4079 1.0000
5.750 0.7914 0.01406 0.00664 -0.0136 0.3974 1.0000
6.000 0.8159 0.01435 0.00696 -0.0132 0.3866 1.0000
6.250 0.8398 0.01472 0.00730 -0.0127 0.3769 1.0000
6.500 0.8636 0.01505 0.00761 -0.0122 0.3668 1.0000
6.750 0.8873 0.01538 0.00797 -0.0117 0.3565 1.0000
7.000 0.9104 0.01575 0.00828 -0.0111 0.3453 1.0000
7.250 0.9340 0.01598 0.00855 -0.0107 0.3320 1.0000
7.500 0.9578 0.01626 0.00887 -0.0103 0.3190 1.0000
7.750 0.9818 0.01660 0.00921 -0.0100 0.3076 1.0000
8.000 1.0060 0.01692 0.00953 -0.0098 0.2959 1.0000
8.250 1.0306 0.01720 0.00991 -0.0096 0.2833 1.0000
8.500 1.0549 0.01753 0.01029 -0.0095 0.2705 1.0000
8.750 1.0788 0.01788 0.01068 -0.0094 0.2565 1.0000
9.000 1.1022 0.01826 0.01109 -0.0092 0.2405 1.0000
9.250 1.1249 0.01870 0.01156 -0.0090 0.2211 1.0000
9.500 1.1454 0.01931 0.01212 -0.0087 0.1965 1.0000
9.750 1.1625 0.02025 0.01291 -0.0081 0.1597 1.0000
10.000 1.1715 0.02189 0.01423 -0.0069 0.1166 1.0000
10.250 1.1765 0.02377 0.01588 -0.0053 0.0915 1.0000
10.500 1.1796 0.02544 0.01748 -0.0032 0.0795 1.0000
10.750 1.1851 0.02708 0.01911 -0.0016 0.0718 1.0000
11.000 1.1920 0.02870 0.02078 -0.0002 0.0662 1.0000
11.250 1.1957 0.03063 0.02268 0.0011 0.0622 1.0000
11.500 1.2034 0.03232 0.02445 0.0021 0.0588 1.0000
11.750 1.2102 0.03411 0.02628 0.0030 0.0561 1.0000
12.000 1.2133 0.03629 0.02841 0.0042 0.0539 1.0000
12.250 1.2221 0.03803 0.03027 0.0049 0.0518 1.0000
12.500 1.2299 0.03985 0.03217 0.0056 0.0498 1.0000
12.750 1.2372 0.04175 0.03406 0.0063 0.0480 1.0000
13.000 1.2456 0.04367 0.03594 0.0073 0.0464 1.0000
13.250 1.2542 0.04555 0.03797 0.0079 0.0452 1.0000
13.500 1.2629 0.04746 0.03999 0.0085 0.0440 1.0000
13.750 1.2719 0.04936 0.04196 0.0091 0.0429 1.0000
14.000 1.2820 0.05119 0.04381 0.0097 0.0418 1.0000
14.250 1.3015 0.05260 0.04509 0.0110 0.0404 1.0000
14.500 1.3029 0.05519 0.04791 0.0112 0.0398 1.0000
14.750 1.3046 0.05789 0.05082 0.0113 0.0391 1.0000
15.000 1.3066 0.06063 0.05374 0.0114 0.0383 1.0000
15.250 1.3089 0.06341 0.05667 0.0114 0.0377 1.0000
15.500 1.3114 0.06625 0.05964 0.0114 0.0371 1.0000
15.750 1.3118 0.06934 0.06287 0.0111 0.0366 1.0000
16.000 1.3117 0.07254 0.06620 0.0108 0.0362 1.0000
16.250 1.3125 0.07575 0.06952 0.0104 0.0358 1.0000
16.500 1.3141 0.07903 0.07290 0.0102 0.0354 1.0000
16.750 1.3134 0.08284 0.07683 0.0099 0.0351 1.0000
17.000 1.3020 0.08790 0.08209 0.0084 0.0349 1.0000
17.250 1.2849 0.09375 0.08818 0.0058 0.0349 1.0000
17.500 1.2665 0.10012 0.09477 0.0026 0.0349 1.0000
17.750 1.2468 0.10707 0.10196 -0.0012 0.0349 1.0000
18.000 1.2262 0.11460 0.10970 -0.0056 0.0349 1.0000
18.250 1.2024 0.12311 0.11846 -0.0112 0.0350 1.0000
18.500 0.6541 0.18769 0.18423 -0.0301 0.0707 1.0000
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