GOE 12K AIRFOIL (goe12k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 12K AIRFOIL (goe12k-il) Reynolds number: 1,000,000 Max Cl/Cd: 146.69 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe12k-il-1000000.txt Download as CSV file: xf-goe12k-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9180 0.03786 0.03514 -0.1439 0.9786 0.0153
-15.250 -0.9273 0.03288 0.02991 -0.1483 0.9765 0.0155
-15.000 -0.9415 0.03015 0.02700 -0.1456 0.9688 0.0156
-14.750 -0.9372 0.02797 0.02468 -0.1450 0.9663 0.0160
-14.500 -0.9395 0.02673 0.02334 -0.1412 0.9595 0.0164
-14.250 -0.9263 0.02536 0.02185 -0.1403 0.9566 0.0168
-14.000 -0.9099 0.02389 0.02023 -0.1400 0.9549 0.0173
-13.750 -0.8891 0.02277 0.01898 -0.1400 0.9539 0.0179
-13.500 -0.8827 0.02194 0.01802 -0.1367 0.9478 0.0182
-13.250 -0.8688 0.02056 0.01650 -0.1355 0.9454 0.0189
-13.000 -0.8485 0.01954 0.01541 -0.1351 0.9440 0.0197
-12.750 -0.8238 0.01875 0.01454 -0.1354 0.9430 0.0204
-12.500 -0.7973 0.01800 0.01368 -0.1359 0.9423 0.0212
-12.250 -0.7693 0.01731 0.01285 -0.1368 0.9416 0.0219
-12.000 -0.7552 0.01661 0.01210 -0.1346 0.9376 0.0230
-11.750 -0.7304 0.01618 0.01164 -0.1345 0.9356 0.0242
-11.500 -0.7035 0.01575 0.01114 -0.1348 0.9342 0.0252
-11.250 -0.6741 0.01535 0.01065 -0.1356 0.9331 0.0263
-11.000 -0.6438 0.01498 0.01029 -0.1367 0.9321 0.0279
-10.750 -0.6101 0.01488 0.01018 -0.1382 0.9314 0.0291
-10.500 -0.5759 0.01470 0.00994 -0.1399 0.9307 0.0304
-10.250 -0.5425 0.01431 0.00947 -0.1416 0.9298 0.0315
-10.000 -0.5067 0.01430 0.00950 -0.1436 0.9291 0.0328
-9.750 -0.4776 0.01432 0.00951 -0.1441 0.9274 0.0337
-9.500 -0.4550 0.01435 0.00952 -0.1431 0.9252 0.0346
-9.250 -0.4287 0.01426 0.00937 -0.1430 0.9231 0.0355
-9.000 -0.3997 0.01418 0.00922 -0.1435 0.9211 0.0363
-8.750 -0.3705 0.01358 0.00852 -0.1443 0.9193 0.0375
-8.500 -0.3352 0.01354 0.00850 -0.1463 0.9179 0.0385
-8.250 -0.2983 0.01351 0.00846 -0.1486 0.9167 0.0394
-8.000 -0.2611 0.01345 0.00837 -0.1510 0.9157 0.0405
-7.750 -0.2242 0.01332 0.00818 -0.1533 0.9147 0.0417
-7.500 -0.2124 0.01322 0.00804 -0.1499 0.9121 0.0423
-7.250 -0.1924 0.01319 0.00797 -0.1482 0.9099 0.0429
-7.000 -0.1683 0.01275 0.00744 -0.1477 0.9080 0.0438
-6.750 -0.1420 0.01206 0.00673 -0.1478 0.9063 0.0451
-6.500 -0.1135 0.01185 0.00651 -0.1483 0.9048 0.0460
-6.250 -0.0842 0.01165 0.00629 -0.1488 0.9035 0.0469
-6.000 -0.0527 0.01143 0.00603 -0.1499 0.9022 0.0479
-5.750 -0.0200 0.01121 0.00578 -0.1512 0.9009 0.0489
-5.500 0.0110 0.01100 0.00553 -0.1521 0.8995 0.0497
-5.250 0.0210 0.01083 0.00535 -0.1481 0.8972 0.0502
-5.000 0.0385 0.01068 0.00518 -0.1459 0.8948 0.0507
-4.750 0.0616 0.01055 0.00502 -0.1449 0.8928 0.0511
-4.500 0.0882 0.01031 0.00475 -0.1448 0.8907 0.0518
-4.250 0.1141 0.00965 0.00405 -0.1446 0.8888 0.0533
-4.000 0.1440 0.00938 0.00377 -0.1452 0.8868 0.0543
-3.750 0.1776 0.00921 0.00358 -0.1467 0.8846 0.0551
-3.500 0.1885 0.00910 0.00349 -0.1429 0.8820 0.0559
-3.250 0.2026 0.00898 0.00336 -0.1398 0.8791 0.0566
-3.000 0.2241 0.00884 0.00322 -0.1383 0.8767 0.0574
-2.750 0.2500 0.00869 0.00306 -0.1380 0.8746 0.0584
-2.500 0.2787 0.00855 0.00291 -0.1382 0.8727 0.0594
-2.250 0.3096 0.00843 0.00277 -0.1390 0.8707 0.0602
-2.000 0.3417 0.00837 0.00270 -0.1401 0.8685 0.0610
-1.750 0.3488 0.00830 0.00265 -0.1352 0.8655 0.0614
-1.500 0.3637 0.00815 0.00249 -0.1322 0.8624 0.0630
-1.250 0.3864 0.00801 0.00235 -0.1311 0.8598 0.0655
-1.000 0.4139 0.00790 0.00225 -0.1310 0.8576 0.0682
-0.750 0.4437 0.00781 0.00217 -0.1315 0.8556 0.0704
-0.500 0.4771 0.00776 0.00212 -0.1329 0.8537 0.0740
-0.250 0.4842 0.00766 0.00210 -0.1280 0.8503 0.0840
0.000 0.4918 0.00747 0.00207 -0.1234 0.8465 0.1335
0.250 0.5110 0.00722 0.00202 -0.1214 0.8433 0.1991
0.500 0.5316 0.00678 0.00200 -0.1201 0.8405 0.3583
0.750 0.5468 0.00619 0.00205 -0.1175 0.8370 0.5885
1.000 0.5360 0.00582 0.00214 -0.1085 0.8321 0.7358
1.250 0.7307 0.00582 0.00276 -0.1472 0.8299 0.9658
1.500 0.7545 0.00590 0.00281 -0.1459 0.8196 0.9797
1.750 0.7920 0.00596 0.00284 -0.1479 0.8046 0.9880
2.000 0.8362 0.00604 0.00286 -0.1516 0.7867 0.9947
2.250 0.8752 0.00603 0.00279 -0.1542 0.7696 0.9983
2.500 0.8963 0.00611 0.00277 -0.1527 0.7458 1.0000
2.750 0.8990 0.00627 0.00283 -0.1470 0.7229 1.0000
3.000 0.9011 0.00648 0.00292 -0.1412 0.6967 1.0000
3.250 0.8928 0.00686 0.00310 -0.1331 0.6481 1.0000
3.500 0.8583 0.00780 0.00356 -0.1193 0.5428 1.0000
3.750 0.8389 0.00879 0.00411 -0.1093 0.4548 1.0000
4.000 0.8481 0.00918 0.00437 -0.1054 0.4258 1.0000
4.250 0.8584 0.00956 0.00464 -0.1018 0.3979 1.0000
4.500 0.8702 0.00991 0.00489 -0.0986 0.3729 1.0000
4.750 0.8827 0.01027 0.00514 -0.0955 0.3437 1.0000
5.000 0.8911 0.01081 0.00546 -0.0917 0.2954 1.0000
5.250 0.8943 0.01157 0.00591 -0.0870 0.2328 1.0000
5.500 0.9001 0.01235 0.00639 -0.0829 0.1740 1.0000
5.750 0.9096 0.01303 0.00683 -0.0795 0.1274 1.0000
6.000 0.9229 0.01357 0.00721 -0.0769 0.0997 1.0000
6.250 0.9394 0.01397 0.00754 -0.0749 0.0867 1.0000
6.500 0.9571 0.01432 0.00786 -0.0731 0.0790 1.0000
6.750 0.9744 0.01470 0.00820 -0.0713 0.0733 1.0000
7.000 0.9922 0.01506 0.00855 -0.0695 0.0690 1.0000
7.250 1.0113 0.01535 0.00886 -0.0680 0.0669 1.0000
7.500 1.0298 0.01568 0.00920 -0.0665 0.0647 1.0000
7.750 1.0472 0.01609 0.00958 -0.0647 0.0609 1.0000
8.000 1.0642 0.01651 0.01002 -0.0630 0.0583 1.0000
8.250 1.0835 0.01681 0.01035 -0.0616 0.0570 1.0000
8.500 1.1024 0.01713 0.01068 -0.0602 0.0549 1.0000
8.750 1.1203 0.01752 0.01107 -0.0587 0.0526 1.0000
9.000 1.1359 0.01805 0.01158 -0.0568 0.0488 1.0000
9.250 1.1553 0.01836 0.01192 -0.0555 0.0477 1.0000
9.500 1.1741 0.01869 0.01227 -0.0542 0.0453 1.0000
9.750 1.1911 0.01914 0.01270 -0.0527 0.0424 1.0000
10.000 1.2081 0.01960 0.01317 -0.0511 0.0399 1.0000
10.250 1.2258 0.02001 0.01360 -0.0496 0.0373 1.0000
10.500 1.2417 0.02056 0.01412 -0.0479 0.0341 1.0000
10.750 1.2586 0.02102 0.01461 -0.0464 0.0319 1.0000
11.000 1.2739 0.02160 0.01516 -0.0448 0.0293 1.0000
11.250 1.2886 0.02223 0.01581 -0.0429 0.0272 1.0000
11.500 1.3041 0.02279 0.01640 -0.0413 0.0257 1.0000
11.750 1.3178 0.02349 0.01711 -0.0394 0.0241 1.0000
12.000 1.3311 0.02421 0.01786 -0.0376 0.0228 1.0000
12.250 1.3455 0.02487 0.01857 -0.0358 0.0218 1.0000
12.500 1.3594 0.02556 0.01929 -0.0341 0.0208 1.0000
12.750 1.3708 0.02643 0.02019 -0.0321 0.0198 1.0000
13.000 1.3805 0.02742 0.02123 -0.0299 0.0189 1.0000
13.250 1.3942 0.02813 0.02200 -0.0283 0.0182 1.0000
13.500 1.4060 0.02898 0.02291 -0.0265 0.0177 1.0000
13.750 1.4175 0.02986 0.02385 -0.0247 0.0172 1.0000
14.000 1.4277 0.03086 0.02488 -0.0228 0.0165 1.0000
14.250 1.4337 0.03217 0.02625 -0.0205 0.0159 1.0000
14.500 1.4387 0.03357 0.02773 -0.0182 0.0154 1.0000
14.750 1.4492 0.03458 0.02881 -0.0165 0.0151 1.0000
15.000 1.4596 0.03561 0.02991 -0.0149 0.0147 1.0000
15.250 1.4659 0.03697 0.03136 -0.0130 0.0145 1.0000
15.500 1.4758 0.03808 0.03252 -0.0115 0.0139 1.0000
15.750 1.4818 0.03950 0.03401 -0.0097 0.0137 1.0000
16.000 1.4878 0.04098 0.03554 -0.0080 0.0133 1.0000
16.250 1.4888 0.04291 0.03755 -0.0061 0.0130 1.0000
16.500 1.4848 0.04537 0.04011 -0.0040 0.0127 1.0000
16.750 1.4799 0.04799 0.04284 -0.0020 0.0125 1.0000
17.000 1.4878 0.04946 0.04439 -0.0010 0.0122 1.0000
17.250 1.4893 0.05161 0.04664 0.0003 0.0121 1.0000
17.500 1.4909 0.05380 0.04894 0.0014 0.0119 1.0000
17.750 1.4884 0.05650 0.05174 0.0025 0.0118 1.0000
18.000 1.4877 0.05909 0.05444 0.0033 0.0116 1.0000
18.250 1.4842 0.06206 0.05751 0.0040 0.0114 1.0000
18.500 1.4838 0.06478 0.06032 0.0044 0.0112 1.0000
18.750 1.4769 0.06843 0.06408 0.0046 0.0110 1.0000
19.000 1.4694 0.07229 0.06804 0.0044 0.0109 1.0000
19.250 1.4599 0.07661 0.07249 0.0039 0.0109 1.0000
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