ONERA OA212 AIRFOIL (oa212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA OA212 AIRFOIL (oa212-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.64 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oa212-il-1000000.txt Download as CSV file: xf-oa212-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -1.2367 0.05043 0.04764 -0.0173 0.9245 0.0178
-14.250 -1.2569 0.04557 0.04257 -0.0180 0.9208 0.0178
-14.000 -1.2695 0.04233 0.03915 -0.0166 0.9173 0.0179
-13.750 -1.2767 0.03993 0.03657 -0.0144 0.9139 0.0179
-13.500 -1.2870 0.03757 0.03402 -0.0110 0.9101 0.0180
-13.250 -1.3001 0.03405 0.03022 -0.0075 0.9063 0.0182
-13.000 -1.2971 0.03180 0.02777 -0.0051 0.9033 0.0184
-12.750 -1.2859 0.03031 0.02615 -0.0034 0.9005 0.0185
-12.500 -1.2696 0.02906 0.02481 -0.0023 0.8978 0.0187
-12.250 -1.2514 0.02801 0.02368 -0.0013 0.8948 0.0189
-12.000 -1.2321 0.02710 0.02269 -0.0004 0.8917 0.0191
-11.750 -1.2121 0.02627 0.02176 0.0005 0.8889 0.0193
-11.500 -1.1916 0.02545 0.02084 0.0014 0.8863 0.0196
-11.250 -1.1699 0.02461 0.01991 0.0021 0.8836 0.0199
-11.000 -1.1477 0.02368 0.01887 0.0027 0.8805 0.0201
-10.750 -1.1253 0.02280 0.01788 0.0034 0.8772 0.0204
-10.500 -1.1024 0.02200 0.01696 0.0040 0.8742 0.0206
-10.250 -1.0791 0.02127 0.01611 0.0046 0.8713 0.0209
-10.000 -1.0549 0.02065 0.01538 0.0052 0.8683 0.0211
-9.750 -1.0310 0.01964 0.01426 0.0056 0.8653 0.0214
-9.500 -1.0079 0.01852 0.01306 0.0061 0.8618 0.0218
-9.250 -0.9826 0.01790 0.01238 0.0065 0.8583 0.0222
-9.000 -0.9568 0.01739 0.01183 0.0068 0.8552 0.0226
-8.750 -0.9309 0.01693 0.01130 0.0071 0.8519 0.0230
-8.500 -0.9038 0.01644 0.01077 0.0072 0.8486 0.0234
-8.250 -0.8766 0.01597 0.01024 0.0073 0.8448 0.0239
-8.000 -0.8495 0.01554 0.00974 0.0075 0.8411 0.0243
-7.750 -0.8221 0.01520 0.00932 0.0076 0.8376 0.0247
-7.500 -0.7964 0.01444 0.00850 0.0079 0.8339 0.0255
-7.250 -0.7684 0.01401 0.00807 0.0078 0.8301 0.0262
-7.000 -0.7403 0.01367 0.00770 0.0078 0.8261 0.0268
-6.750 -0.7122 0.01333 0.00732 0.0078 0.8222 0.0275
-6.500 -0.6843 0.01302 0.00695 0.0079 0.8183 0.0282
-6.250 -0.6557 0.01275 0.00663 0.0078 0.8143 0.0288
-6.000 -0.6277 0.01219 0.00607 0.0078 0.8101 0.0300
-5.750 -0.5991 0.01190 0.00577 0.0077 0.8059 0.0310
-5.500 -0.5706 0.01165 0.00548 0.0076 0.8018 0.0321
-5.250 -0.5416 0.01146 0.00524 0.0075 0.7975 0.0330
-5.000 -0.5128 0.01106 0.00486 0.0073 0.7929 0.0348
-4.750 -0.4837 0.01083 0.00462 0.0072 0.7872 0.0364
-4.500 -0.4549 0.01065 0.00438 0.0071 0.7807 0.0379
-4.250 -0.4256 0.01032 0.00407 0.0069 0.7742 0.0402
-4.000 -0.3963 0.01014 0.00387 0.0067 0.7678 0.0424
-3.750 -0.3670 0.00992 0.00363 0.0065 0.7614 0.0453
-3.500 -0.3373 0.00973 0.00347 0.0062 0.7546 0.0486
-3.250 -0.3079 0.00954 0.00326 0.0060 0.7480 0.0524
-3.000 -0.2781 0.00940 0.00312 0.0057 0.7423 0.0564
-2.750 -0.2483 0.00920 0.00297 0.0054 0.7365 0.0618
-2.500 -0.2185 0.00908 0.00283 0.0051 0.7304 0.0672
-2.250 -0.1885 0.00894 0.00272 0.0047 0.7245 0.0732
-2.000 -0.1586 0.00879 0.00260 0.0043 0.7180 0.0798
-1.750 -0.1285 0.00871 0.00250 0.0040 0.7116 0.0855
-1.500 -0.0984 0.00855 0.00240 0.0036 0.7048 0.0944
-1.250 -0.0683 0.00845 0.00230 0.0032 0.6975 0.1028
-1.000 -0.0381 0.00835 0.00222 0.0027 0.6906 0.1121
-0.750 -0.0078 0.00822 0.00214 0.0023 0.6828 0.1264
-0.500 0.0225 0.00810 0.00206 0.0018 0.6745 0.1453
-0.250 0.0528 0.00792 0.00199 0.0013 0.6653 0.1783
0.000 0.0830 0.00762 0.00193 0.0007 0.6564 0.2546
0.250 0.1132 0.00706 0.00186 -0.0002 0.6462 0.4065
0.500 0.1386 0.00557 0.00192 -0.0001 0.6356 0.8573
0.750 0.1671 0.00568 0.00201 0.0001 0.6228 0.8869
1.000 0.1963 0.00579 0.00208 0.0000 0.6092 0.9015
1.250 0.2245 0.00592 0.00217 0.0003 0.5938 0.9117
1.500 0.2532 0.00605 0.00222 0.0003 0.5748 0.9193
1.750 0.2811 0.00620 0.00229 0.0005 0.5534 0.9259
2.000 0.3108 0.00638 0.00237 0.0002 0.5273 0.9320
2.250 0.3375 0.00655 0.00242 0.0006 0.4954 0.9373
2.500 0.3644 0.00680 0.00253 0.0009 0.4615 0.9448
2.750 0.3887 0.00698 0.00259 0.0018 0.4335 0.9514
3.000 0.4136 0.00715 0.00267 0.0027 0.4113 0.9590
3.250 0.4333 0.00718 0.00264 0.0047 0.3943 0.9682
3.500 0.4579 0.00726 0.00265 0.0056 0.3798 0.9745
3.750 0.4878 0.00737 0.00270 0.0050 0.3667 0.9762
4.000 0.5183 0.00748 0.00277 0.0044 0.3562 0.9774
4.250 0.5487 0.00763 0.00286 0.0037 0.3457 0.9786
4.500 0.5789 0.00772 0.00293 0.0031 0.3373 0.9800
4.750 0.6091 0.00787 0.00303 0.0024 0.3283 0.9813
5.000 0.6394 0.00797 0.00312 0.0018 0.3209 0.9824
5.250 0.6695 0.00814 0.00324 0.0011 0.3122 0.9834
5.500 0.7004 0.00823 0.00332 0.0004 0.3052 0.9845
6.000 0.7622 0.00855 0.00356 -0.0013 0.2826 0.9868
6.250 0.7929 0.00871 0.00369 -0.0022 0.2713 0.9878
6.500 0.8234 0.00892 0.00384 -0.0030 0.2611 0.9889
6.750 0.8541 0.00907 0.00398 -0.0038 0.2520 0.9900
7.000 0.8846 0.00928 0.00415 -0.0046 0.2416 0.9911
7.250 0.9148 0.00952 0.00435 -0.0055 0.2291 0.9922
7.500 0.9451 0.00978 0.00455 -0.0063 0.2152 0.9936
7.750 0.9761 0.01010 0.00480 -0.0074 0.1991 0.9945
8.000 1.0068 0.01046 0.00508 -0.0085 0.1800 0.9954
8.250 1.0365 0.01098 0.00545 -0.0096 0.1552 0.9965
8.500 1.0653 0.01159 0.00590 -0.0106 0.1283 0.9978
8.750 1.0929 0.01228 0.00642 -0.0114 0.1006 0.9999
9.000 1.1159 0.01299 0.00698 -0.0113 0.0766 1.0000
9.250 1.1394 0.01371 0.00757 -0.0114 0.0579 1.0000
9.500 1.1635 0.01438 0.00815 -0.0115 0.0458 1.0000
9.750 1.1882 0.01496 0.00869 -0.0117 0.0391 1.0000
10.000 1.2126 0.01556 0.00927 -0.0118 0.0346 1.0000
10.250 1.2372 0.01610 0.00981 -0.0120 0.0318 1.0000
10.500 1.2609 0.01671 0.01043 -0.0120 0.0294 1.0000
10.750 1.2847 0.01726 0.01100 -0.0121 0.0276 1.0000
11.000 1.3059 0.01805 0.01180 -0.0121 0.0257 1.0000
11.250 1.3288 0.01861 0.01240 -0.0121 0.0247 1.0000
11.500 1.3494 0.01929 0.01311 -0.0120 0.0237 1.0000
11.750 1.3651 0.02014 0.01399 -0.0112 0.0227 1.0000
12.000 1.3781 0.02120 0.01509 -0.0102 0.0218 1.0000
12.250 1.3950 0.02199 0.01594 -0.0096 0.0213 1.0000
12.500 1.4107 0.02291 0.01690 -0.0090 0.0206 1.0000
12.750 1.4252 0.02391 0.01795 -0.0083 0.0201 1.0000
13.000 1.4379 0.02508 0.01917 -0.0076 0.0195 1.0000
13.250 1.4468 0.02659 0.02072 -0.0068 0.0190 1.0000
13.500 1.4522 0.02844 0.02264 -0.0059 0.0185 1.0000
13.750 1.4646 0.02971 0.02398 -0.0054 0.0182 1.0000
14.000 1.4753 0.03116 0.02550 -0.0049 0.0178 1.0000
14.250 1.4842 0.03279 0.02720 -0.0045 0.0174 1.0000
14.500 1.4919 0.03459 0.02906 -0.0041 0.0171 1.0000
14.750 1.4979 0.03659 0.03113 -0.0038 0.0168 1.0000
15.000 1.5023 0.03881 0.03342 -0.0036 0.0165 1.0000
15.250 1.5041 0.04137 0.03605 -0.0036 0.0163 1.0000
15.500 1.5025 0.04438 0.03914 -0.0037 0.0160 1.0000
15.750 1.4965 0.04804 0.04290 -0.0040 0.0158 1.0000
16.000 1.4861 0.05245 0.04742 -0.0048 0.0156 1.0000
16.250 1.4802 0.05644 0.05152 -0.0057 0.0154 1.0000
16.500 1.4779 0.06013 0.05530 -0.0067 0.0153 1.0000
16.750 1.4743 0.06409 0.05937 -0.0078 0.0152 1.0000
17.000 1.4689 0.06835 0.06374 -0.0092 0.0151 1.0000
17.250 1.4619 0.07297 0.06846 -0.0107 0.0150 1.0000
17.500 1.4540 0.07778 0.07338 -0.0124 0.0149 1.0000
17.750 1.4449 0.08282 0.07853 -0.0143 0.0148 1.0000
18.000 1.4352 0.08799 0.08379 -0.0162 0.0147 1.0000
18.250 1.4254 0.09322 0.08912 -0.0182 0.0146 1.0000
18.500 1.4157 0.09847 0.09447 -0.0203 0.0144 1.0000
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Polar data table (+)
Polar graphs
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