GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.48 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe217-il-1000000.txt Download as CSV file: xf-goe217-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 217 (MVA MK.12) 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3814 0.08683 0.08471 -0.0720 0.9980 0.0322
-12.750 -0.4282 0.07327 0.07091 -0.0872 0.9882 0.0322
-12.500 -0.4507 0.06444 0.06188 -0.0996 0.9604 0.0322
-12.250 -0.4681 0.05835 0.05546 -0.1078 0.9111 0.0322
-12.000 -0.4850 0.05402 0.05089 -0.1129 0.8821 0.0322
-11.750 -0.5038 0.04576 0.04242 -0.1178 0.8645 0.0327
-11.500 -0.4888 0.04359 0.04016 -0.1193 0.8477 0.0329
-11.250 -0.4733 0.04119 0.03765 -0.1224 0.8291 0.0330
-11.000 -0.4550 0.03870 0.03502 -0.1265 0.8095 0.0331
-10.750 -0.4334 0.03631 0.03247 -0.1309 0.7895 0.0333
-10.500 -0.4087 0.03406 0.03006 -0.1355 0.7705 0.0335
-10.250 -0.3821 0.03209 0.02792 -0.1395 0.7535 0.0338
-10.000 -0.3545 0.03033 0.02597 -0.1429 0.7373 0.0341
-9.750 -0.3277 0.02619 0.02134 -0.1472 0.7236 0.0311
-9.500 -0.2995 0.02462 0.01959 -0.1489 0.7105 0.0310
-9.250 -0.2724 0.02298 0.01779 -0.1498 0.6969 0.0305
-9.000 -0.2439 0.02175 0.01643 -0.1507 0.6846 0.0304
-8.750 -0.2152 0.02079 0.01532 -0.1515 0.6706 0.0303
-8.500 -0.1856 0.01993 0.01438 -0.1523 0.6586 0.0304
-8.250 -0.1563 0.01920 0.01354 -0.1529 0.6460 0.0304
-8.000 -0.1267 0.01851 0.01278 -0.1535 0.6341 0.0305
-7.750 -0.0971 0.01791 0.01210 -0.1540 0.6221 0.0306
-7.500 -0.0673 0.01735 0.01148 -0.1544 0.6100 0.0306
-7.250 -0.0373 0.01685 0.01091 -0.1549 0.5987 0.0307
-7.000 -0.0070 0.01638 0.01038 -0.1555 0.5873 0.0308
-6.750 0.0237 0.01595 0.00989 -0.1561 0.5768 0.0309
-6.500 0.0547 0.01554 0.00943 -0.1568 0.5663 0.0310
-6.250 0.0861 0.01516 0.00899 -0.1576 0.5564 0.0312
-6.000 0.1181 0.01478 0.00856 -0.1585 0.5476 0.0314
-5.750 0.1501 0.01446 0.00817 -0.1594 0.5382 0.0316
-5.500 0.1827 0.01417 0.00783 -0.1604 0.5319 0.0319
-5.250 0.2149 0.01397 0.00757 -0.1612 0.5248 0.0322
-5.000 0.2483 0.01346 0.00701 -0.1627 0.5169 0.0325
-4.750 0.2830 0.01291 0.00644 -0.1644 0.5119 0.0329
-4.500 0.3166 0.01254 0.00604 -0.1657 0.5063 0.0334
-4.250 0.3494 0.01228 0.00573 -0.1668 0.5003 0.0338
-4.000 0.3818 0.01208 0.00547 -0.1677 0.4941 0.0342
-3.750 0.4145 0.01184 0.00521 -0.1686 0.4904 0.0346
-3.500 0.4468 0.01165 0.00498 -0.1694 0.4857 0.0351
-3.250 0.4787 0.01150 0.00478 -0.1700 0.4807 0.0355
-3.000 0.5101 0.01141 0.00462 -0.1706 0.4750 0.0360
-2.750 0.5418 0.01129 0.00448 -0.1712 0.4717 0.0364
-2.500 0.5740 0.01110 0.00427 -0.1719 0.4687 0.0371
-2.250 0.6058 0.01095 0.00410 -0.1725 0.4651 0.0381
-2.000 0.6370 0.01088 0.00400 -0.1730 0.4614 0.0393
-1.750 0.6678 0.01086 0.00393 -0.1733 0.4574 0.0407
-1.500 0.6984 0.01086 0.00388 -0.1737 0.4528 0.0423
-1.250 0.7297 0.01078 0.00381 -0.1741 0.4509 0.0449
-1.000 0.7610 0.01068 0.00375 -0.1746 0.4485 0.0552
-0.750 0.7970 0.00990 0.00346 -0.1768 0.4455 0.2447
-0.500 0.8282 0.00974 0.00344 -0.1774 0.4418 0.2976
-0.250 0.8584 0.00973 0.00348 -0.1778 0.4368 0.3336
0.000 0.8883 0.00977 0.00356 -0.1780 0.4319 0.3602
0.250 0.9186 0.00977 0.00361 -0.1782 0.4294 0.3797
0.500 0.9486 0.00981 0.00367 -0.1783 0.4267 0.3929
0.750 0.9783 0.00988 0.00374 -0.1784 0.4233 0.4031
1.000 1.0077 0.00997 0.00383 -0.1785 0.4195 0.4125
1.250 1.0367 0.01011 0.00394 -0.1785 0.4154 0.4205
1.500 1.0660 0.01023 0.00404 -0.1785 0.4122 0.4275
1.750 1.0958 0.01027 0.00413 -0.1787 0.4095 0.4355
2.000 1.1252 0.01035 0.00422 -0.1787 0.4064 0.4412
2.250 1.1544 0.01045 0.00430 -0.1788 0.4033 0.4449
2.500 1.1833 0.01057 0.00439 -0.1788 0.4001 0.4480
2.750 1.2118 0.01070 0.00452 -0.1787 0.3961 0.4529
3.000 1.2406 0.01082 0.00465 -0.1787 0.3930 0.4571
3.250 1.2699 0.01089 0.00474 -0.1788 0.3908 0.4612
3.500 1.2989 0.01098 0.00485 -0.1788 0.3880 0.4649
3.750 1.3275 0.01109 0.00495 -0.1788 0.3846 0.4677
4.000 1.3558 0.01122 0.00506 -0.1788 0.3806 0.4709
4.250 1.3834 0.01139 0.00523 -0.1786 0.3759 0.4762
4.500 1.4120 0.01148 0.00536 -0.1786 0.3732 0.4808
4.750 1.4405 0.01158 0.00549 -0.1786 0.3698 0.4852
5.000 1.4684 0.01172 0.00562 -0.1785 0.3653 0.4889
5.250 1.4955 0.01193 0.00578 -0.1783 0.3595 0.4911
5.500 1.5233 0.01203 0.00591 -0.1782 0.3540 0.4955
5.750 1.5507 0.01217 0.00606 -0.1780 0.3470 0.4992
6.000 1.5767 0.01241 0.00626 -0.1777 0.3388 0.5023
6.250 1.6037 0.01258 0.00643 -0.1775 0.3305 0.5052
6.500 1.6288 0.01287 0.00666 -0.1770 0.3192 0.5081
6.750 1.6528 0.01324 0.00695 -0.1763 0.3034 0.5110
7.000 1.6747 0.01374 0.00733 -0.1754 0.2821 0.5131
7.250 1.6934 0.01444 0.00786 -0.1739 0.2573 0.5164
7.500 1.7118 0.01510 0.00842 -0.1724 0.2377 0.5199
7.750 1.7302 0.01572 0.00896 -0.1709 0.2232 0.5229
8.000 1.7491 0.01626 0.00946 -0.1695 0.2129 0.5259
8.250 1.7680 0.01675 0.00992 -0.1680 0.2053 0.5291
8.500 1.7852 0.01727 0.01042 -0.1663 0.1986 0.5321
8.750 1.8015 0.01778 0.01092 -0.1644 0.1931 0.5346
9.000 1.8151 0.01823 0.01138 -0.1620 0.1889 0.5370
9.250 1.8272 0.01883 0.01200 -0.1594 0.1842 0.5410
9.500 1.8404 0.01949 0.01267 -0.1572 0.1797 0.5443
9.750 1.8562 0.02004 0.01326 -0.1555 0.1767 0.5476
10.000 1.8700 0.02073 0.01397 -0.1536 0.1734 0.5511
10.250 1.8816 0.02157 0.01482 -0.1515 0.1700 0.5544
10.500 1.8921 0.02253 0.01579 -0.1494 0.1666 0.5570
10.750 1.9071 0.02327 0.01659 -0.1480 0.1649 0.5608
11.000 1.9202 0.02415 0.01753 -0.1465 0.1627 0.5648
11.250 1.9315 0.02520 0.01862 -0.1449 0.1605 0.5684
11.500 1.9409 0.02645 0.01991 -0.1432 0.1580 0.5719
11.750 1.9481 0.02793 0.02142 -0.1415 0.1554 0.5754
12.000 1.9563 0.02940 0.02292 -0.1400 0.1534 0.5785
12.250 1.9675 0.03068 0.02428 -0.1389 0.1520 0.5831
12.500 1.9767 0.03216 0.02584 -0.1378 0.1503 0.5872
12.750 1.9838 0.03389 0.02762 -0.1366 0.1483 0.5912
13.000 1.9880 0.03593 0.02971 -0.1354 0.1462 0.5948
13.250 1.9898 0.03828 0.03210 -0.1342 0.1442 0.5981
13.500 1.9886 0.04101 0.03489 -0.1331 0.1422 0.6014
13.750 1.9928 0.04322 0.03719 -0.1323 0.1410 0.6053
14.000 1.9969 0.04549 0.03955 -0.1315 0.1399 0.6092
14.250 1.9987 0.04803 0.04217 -0.1307 0.1386 0.6129
14.500 1.9988 0.05082 0.04502 -0.1300 0.1370 0.6166
14.750 1.9965 0.05390 0.04817 -0.1293 0.1353 0.6199
15.000 1.9916 0.05731 0.05165 -0.1287 0.1336 0.6235
15.250 1.9840 0.06112 0.05553 -0.1282 0.1318 0.6266
15.500 1.9758 0.06506 0.05954 -0.1277 0.1302 0.6298
15.750 1.9759 0.06801 0.06258 -0.1274 0.1291 0.6334
16.000 1.9750 0.07105 0.06570 -0.1270 0.1276 0.6366
16.250 1.9702 0.07465 0.06938 -0.1268 0.1260 0.6396
16.500 1.9652 0.07829 0.07308 -0.1267 0.1243 0.6426
16.750 1.9575 0.08227 0.07712 -0.1266 0.1223 0.6455
17.000 1.9464 0.08671 0.08162 -0.1266 0.1203 0.6482
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