GOE 12K AIRFOIL (goe12k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 12K AIRFOIL (goe12k-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.61 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe12k-il-1000000-n5.txt Download as CSV file: xf-goe12k-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 12K 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8613 0.03344 0.03042 -0.1493 0.9419 0.0085
-14.500 -0.8694 0.02975 0.02647 -0.1487 0.9357 0.0086
-14.250 -0.8603 0.02733 0.02383 -0.1489 0.9321 0.0088
-14.000 -0.8429 0.02523 0.02154 -0.1499 0.9287 0.0090
-13.750 -0.8215 0.02353 0.01966 -0.1510 0.9255 0.0093
-13.500 -0.7989 0.02190 0.01783 -0.1522 0.9224 0.0096
-13.250 -0.7740 0.02046 0.01623 -0.1536 0.9200 0.0100
-13.000 -0.7504 0.01933 0.01496 -0.1543 0.9174 0.0105
-12.750 -0.7284 0.01846 0.01397 -0.1542 0.9146 0.0108
-12.500 -0.7054 0.01769 0.01308 -0.1543 0.9120 0.0113
-12.250 -0.6818 0.01693 0.01221 -0.1544 0.9097 0.0119
-12.000 -0.6580 0.01613 0.01130 -0.1545 0.9076 0.0126
-11.750 -0.6323 0.01546 0.01052 -0.1549 0.9057 0.0134
-11.250 -0.5864 0.01441 0.00929 -0.1541 0.9019 0.0148
-11.000 -0.5684 0.01388 0.00870 -0.1526 0.8997 0.0159
-10.750 -0.5473 0.01341 0.00818 -0.1517 0.8979 0.0172
-10.500 -0.5246 0.01298 0.00768 -0.1510 0.8963 0.0185
-10.250 -0.5012 0.01250 0.00716 -0.1506 0.8947 0.0210
-10.000 -0.4755 0.01212 0.00675 -0.1506 0.8933 0.0234
-9.750 -0.4477 0.01181 0.00641 -0.1510 0.8919 0.0264
-9.500 -0.4169 0.01164 0.00626 -0.1520 0.8906 0.0300
-9.250 -0.3853 0.01147 0.00605 -0.1531 0.8895 0.0325
-9.000 -0.3555 0.01130 0.00585 -0.1538 0.8881 0.0340
-8.750 -0.3396 0.01125 0.00583 -0.1513 0.8858 0.0355
-8.500 -0.3214 0.01120 0.00578 -0.1492 0.8833 0.0368
-8.250 -0.2994 0.01114 0.00571 -0.1481 0.8811 0.0381
-8.000 -0.2750 0.01104 0.00557 -0.1475 0.8795 0.0391
-7.750 -0.2488 0.01092 0.00541 -0.1473 0.8782 0.0400
-7.500 -0.2206 0.01086 0.00533 -0.1475 0.8769 0.0408
-7.250 -0.1915 0.01078 0.00521 -0.1480 0.8756 0.0413
-7.000 -0.1610 0.01077 0.00517 -0.1487 0.8744 0.0416
-6.750 -0.1342 0.01033 0.00466 -0.1489 0.8730 0.0432
-6.500 -0.1111 0.01019 0.00452 -0.1480 0.8718 0.0444
-6.250 -0.0920 0.01004 0.00437 -0.1461 0.8704 0.0451
-6.000 -0.0726 0.00991 0.00424 -0.1443 0.8688 0.0457
-5.750 -0.0533 0.00973 0.00403 -0.1425 0.8671 0.0462
-5.500 -0.0324 0.00958 0.00386 -0.1410 0.8653 0.0467
-5.250 -0.0108 0.00941 0.00368 -0.1397 0.8635 0.0473
-5.000 0.0131 0.00927 0.00351 -0.1390 0.8619 0.0480
-4.750 0.0391 0.00912 0.00333 -0.1386 0.8605 0.0485
-4.500 0.0669 0.00896 0.00314 -0.1388 0.8590 0.0489
-4.250 0.0994 0.00882 0.00296 -0.1400 0.8570 0.0494
-4.000 0.1107 0.00867 0.00281 -0.1362 0.8547 0.0496
-3.750 0.1241 0.00853 0.00266 -0.1330 0.8517 0.0500
-3.500 0.1427 0.00841 0.00253 -0.1309 0.8490 0.0503
-3.250 0.1638 0.00828 0.00238 -0.1294 0.8467 0.0507
-3.000 0.1885 0.00816 0.00224 -0.1287 0.8443 0.0510
-2.750 0.2161 0.00806 0.00212 -0.1287 0.8425 0.0515
-2.500 0.2396 0.00798 0.00203 -0.1278 0.8405 0.0518
-2.250 0.2526 0.00789 0.00195 -0.1244 0.8370 0.0519
-2.000 0.2716 0.00781 0.00188 -0.1224 0.8340 0.0522
-1.750 0.2928 0.00775 0.00181 -0.1209 0.8312 0.0525
-1.500 0.3162 0.00763 0.00168 -0.1199 0.8288 0.0540
-1.250 0.3428 0.00753 0.00157 -0.1197 0.8266 0.0554
-1.000 0.3569 0.00748 0.00153 -0.1165 0.8227 0.0570
-0.750 0.3753 0.00743 0.00151 -0.1144 0.8190 0.0580
-0.500 0.3966 0.00739 0.00147 -0.1129 0.8154 0.0589
-0.250 0.4207 0.00734 0.00142 -0.1120 0.8124 0.0601
0.000 0.4408 0.00731 0.00142 -0.1103 0.8087 0.0613
0.250 0.4599 0.00729 0.00142 -0.1083 0.8042 0.0627
0.500 0.4803 0.00727 0.00139 -0.1066 0.7986 0.0637
1.000 0.5182 0.00724 0.00141 -0.1026 0.7871 0.0741
1.250 0.5341 0.00716 0.00143 -0.0999 0.7771 0.1157
1.500 0.5506 0.00713 0.00145 -0.0973 0.7662 0.1500
1.750 0.5661 0.00715 0.00148 -0.0945 0.7530 0.1723
2.000 0.5783 0.00711 0.00155 -0.0910 0.7372 0.2370
2.250 0.5889 0.00696 0.00167 -0.0873 0.7225 0.3646
2.750 0.7200 0.00915 0.00402 -0.1079 0.3950 0.9984
3.000 0.7535 0.00943 0.00421 -0.1095 0.3744 1.0000
3.250 0.7686 0.00966 0.00437 -0.1069 0.3574 1.0000
3.500 0.7827 0.00994 0.00456 -0.1041 0.3348 1.0000
3.750 0.7957 0.01028 0.00477 -0.1011 0.3064 1.0000
4.000 0.8052 0.01076 0.00506 -0.0975 0.2632 1.0000
4.250 0.8157 0.01124 0.00537 -0.0942 0.2271 1.0000
4.500 0.8262 0.01177 0.00571 -0.0908 0.1868 1.0000
4.750 0.8411 0.01216 0.00600 -0.0884 0.1621 1.0000
5.250 0.8706 0.01302 0.00661 -0.0836 0.1124 1.0000
5.500 0.8880 0.01336 0.00689 -0.0817 0.0993 1.0000
5.750 0.9057 0.01369 0.00717 -0.0799 0.0886 1.0000
6.000 0.9234 0.01403 0.00746 -0.0782 0.0807 1.0000
6.250 0.9422 0.01431 0.00774 -0.0766 0.0765 1.0000
6.500 0.9611 0.01461 0.00803 -0.0751 0.0733 1.0000
6.750 0.9794 0.01495 0.00834 -0.0735 0.0684 1.0000
7.000 0.9984 0.01525 0.00865 -0.0720 0.0652 1.0000
7.250 1.0168 0.01558 0.00897 -0.0704 0.0623 1.0000
7.500 1.0352 0.01592 0.00930 -0.0689 0.0595 1.0000
7.750 1.0541 0.01625 0.00963 -0.0675 0.0571 1.0000
8.000 1.0732 0.01656 0.00997 -0.0661 0.0561 1.0000
8.250 1.0918 0.01690 0.01032 -0.0647 0.0537 1.0000
8.500 1.1099 0.01728 0.01069 -0.0632 0.0509 1.0000
8.750 1.1278 0.01768 0.01108 -0.0617 0.0477 1.0000
9.000 1.1465 0.01802 0.01146 -0.0603 0.0463 1.0000
9.250 1.1646 0.01840 0.01185 -0.0589 0.0430 1.0000
9.500 1.1815 0.01886 0.01228 -0.0573 0.0381 1.0000
9.750 1.1979 0.01936 0.01274 -0.0557 0.0317 1.0000
10.000 1.2137 0.01990 0.01326 -0.0540 0.0265 1.0000
10.250 1.2288 0.02049 0.01383 -0.0522 0.0227 1.0000
10.500 1.2444 0.02105 0.01440 -0.0505 0.0203 1.0000
10.750 1.2594 0.02165 0.01500 -0.0487 0.0183 1.0000
11.000 1.2750 0.02223 0.01560 -0.0471 0.0164 1.0000
11.250 1.2900 0.02283 0.01623 -0.0454 0.0155 1.0000
11.500 1.3043 0.02349 0.01691 -0.0436 0.0142 1.0000
11.750 1.3192 0.02410 0.01756 -0.0420 0.0133 1.0000
12.000 1.3335 0.02478 0.01826 -0.0403 0.0125 1.0000
12.250 1.3464 0.02554 0.01905 -0.0384 0.0116 1.0000
12.500 1.3604 0.02622 0.01978 -0.0368 0.0111 1.0000
12.750 1.3741 0.02693 0.02054 -0.0351 0.0106 1.0000
13.000 1.3868 0.02772 0.02137 -0.0333 0.0101 1.0000
13.250 1.3987 0.02858 0.02226 -0.0315 0.0096 1.0000
13.500 1.4102 0.02947 0.02320 -0.0297 0.0092 1.0000
13.750 1.4224 0.03031 0.02410 -0.0280 0.0088 1.0000
14.000 1.4336 0.03122 0.02506 -0.0263 0.0085 1.0000
14.250 1.4445 0.03217 0.02606 -0.0246 0.0082 1.0000
14.500 1.4544 0.03321 0.02717 -0.0228 0.0079 1.0000
14.750 1.4629 0.03437 0.02838 -0.0209 0.0076 1.0000
15.000 1.4714 0.03555 0.02962 -0.0191 0.0075 1.0000
15.250 1.4787 0.03684 0.03098 -0.0173 0.0072 1.0000
15.500 1.4875 0.03802 0.03223 -0.0157 0.0071 1.0000
15.750 1.4949 0.03933 0.03362 -0.0140 0.0068 1.0000
16.000 1.5010 0.04079 0.03516 -0.0123 0.0067 1.0000
16.250 1.5072 0.04227 0.03671 -0.0107 0.0065 1.0000
16.500 1.5119 0.04391 0.03843 -0.0092 0.0062 1.0000
16.750 1.5158 0.04566 0.04027 -0.0076 0.0062 1.0000
17.000 1.5194 0.04746 0.04214 -0.0062 0.0060 1.0000
17.250 1.5208 0.04954 0.04430 -0.0047 0.0058 1.0000
17.500 1.5203 0.05186 0.04670 -0.0034 0.0056 1.0000
17.750 1.5191 0.05434 0.04927 -0.0021 0.0056 1.0000
18.000 1.5205 0.05661 0.05165 -0.0012 0.0055 1.0000
18.250 1.5168 0.05949 0.05464 -0.0002 0.0055 1.0000
18.500 1.5136 0.06241 0.05766 0.0005 0.0054 1.0000
18.750 1.5104 0.06545 0.06081 0.0010 0.0053 1.0000
19.000 1.5054 0.06883 0.06430 0.0012 0.0053 1.0000
19.250 1.4979 0.07266 0.06824 0.0011 0.0052 1.0000
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Polar data table (+)
Polar graphs
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