GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Reynolds number: 500,000 Max Cl/Cd: 99.62 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe217-il-500000-n5.txt Download as CSV file: xf-goe217-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4616 0.08357 0.08026 -0.0705 1.0000 0.0254
-13.250 -0.5086 0.06516 0.06143 -0.0878 0.9679 0.0254
-13.000 -0.5125 0.05829 0.05430 -0.0966 0.9307 0.0254
-12.750 -0.5190 0.05348 0.04921 -0.1013 0.8980 0.0255
-12.500 -0.5252 0.04964 0.04512 -0.1046 0.8741 0.0255
-12.250 -0.5280 0.04626 0.04153 -0.1075 0.8531 0.0255
-12.000 -0.5281 0.04323 0.03830 -0.1102 0.8331 0.0256
-11.750 -0.5277 0.04057 0.03544 -0.1127 0.8133 0.0256
-11.500 -0.5163 0.03832 0.03305 -0.1148 0.7946 0.0258
-11.250 -0.5005 0.03645 0.03105 -0.1169 0.7758 0.0259
-11.000 -0.4816 0.03476 0.02923 -0.1192 0.7575 0.0260
-10.750 -0.4604 0.03318 0.02751 -0.1217 0.7401 0.0262
-10.500 -0.4369 0.03167 0.02588 -0.1243 0.7245 0.0263
-10.250 -0.4120 0.03023 0.02432 -0.1267 0.7113 0.0264
-10.000 -0.3858 0.02893 0.02289 -0.1290 0.6981 0.0265
-9.750 -0.3585 0.02775 0.02160 -0.1311 0.6865 0.0266
-9.500 -0.3307 0.02668 0.02043 -0.1329 0.6735 0.0268
-9.250 -0.3021 0.02568 0.01933 -0.1346 0.6615 0.0269
-8.750 -0.2441 0.02393 0.01738 -0.1376 0.6364 0.0272
-8.500 -0.2147 0.02317 0.01650 -0.1389 0.6248 0.0274
-8.250 -0.1847 0.02243 0.01569 -0.1402 0.6140 0.0276
-7.750 -0.1243 0.02113 0.01423 -0.1425 0.5929 0.0280
-7.500 -0.0938 0.02056 0.01357 -0.1436 0.5823 0.0281
-7.250 -0.0627 0.02001 0.01294 -0.1448 0.5729 0.0283
-7.000 -0.0315 0.01950 0.01235 -0.1459 0.5626 0.0285
-6.750 0.0003 0.01901 0.01179 -0.1471 0.5539 0.0287
-6.500 0.0324 0.01852 0.01125 -0.1484 0.5455 0.0289
-6.250 0.0648 0.01808 0.01073 -0.1498 0.5377 0.0291
-6.000 0.0977 0.01764 0.01023 -0.1512 0.5313 0.0292
-5.750 0.1309 0.01720 0.00975 -0.1526 0.5246 0.0294
-5.500 0.1648 0.01665 0.00916 -0.1545 0.5180 0.0298
-5.250 0.1988 0.01619 0.00866 -0.1562 0.5124 0.0302
-5.000 0.2331 0.01575 0.00820 -0.1579 0.5071 0.0306
-4.750 0.2670 0.01536 0.00776 -0.1595 0.5012 0.0309
-4.500 0.3004 0.01503 0.00736 -0.1609 0.4954 0.0312
-4.250 0.3338 0.01472 0.00700 -0.1622 0.4905 0.0316
-4.000 0.3671 0.01442 0.00666 -0.1634 0.4861 0.0319
-3.750 0.4001 0.01416 0.00636 -0.1645 0.4816 0.0323
-3.500 0.4325 0.01395 0.00610 -0.1654 0.4771 0.0327
-3.250 0.4645 0.01380 0.00587 -0.1662 0.4729 0.0331
-3.000 0.4967 0.01361 0.00565 -0.1671 0.4694 0.0335
-2.750 0.5293 0.01339 0.00541 -0.1680 0.4661 0.0341
-2.500 0.5611 0.01325 0.00524 -0.1687 0.4626 0.0347
-2.250 0.5925 0.01315 0.00511 -0.1692 0.4590 0.0355
-2.000 0.6235 0.01309 0.00500 -0.1697 0.4554 0.0364
-1.750 0.6541 0.01307 0.00492 -0.1701 0.4517 0.0375
-1.500 0.6850 0.01302 0.00485 -0.1705 0.4485 0.0391
-1.250 0.7159 0.01297 0.00479 -0.1709 0.4458 0.0410
-1.000 0.7467 0.01293 0.00475 -0.1713 0.4431 0.0437
-0.750 0.7819 0.01234 0.00450 -0.1732 0.4402 0.1843
-0.500 0.8131 0.01221 0.00448 -0.1739 0.4373 0.2265
-0.250 0.8438 0.01215 0.00449 -0.1744 0.4346 0.2588
0.000 0.8743 0.01209 0.00453 -0.1748 0.4319 0.3001
0.250 0.9042 0.01212 0.00462 -0.1751 0.4288 0.3333
0.500 0.9342 0.01212 0.00470 -0.1753 0.4253 0.3575
0.750 0.9638 0.01218 0.00478 -0.1755 0.4202 0.3739
1.000 0.9928 0.01228 0.00488 -0.1755 0.4153 0.3873
1.250 1.0216 0.01241 0.00499 -0.1755 0.4115 0.4018
1.500 1.0503 0.01255 0.00515 -0.1754 0.4081 0.4146
1.750 1.0796 0.01264 0.00526 -0.1755 0.4052 0.4230
2.000 1.1085 0.01274 0.00538 -0.1755 0.4015 0.4287
2.250 1.1371 0.01286 0.00550 -0.1754 0.3969 0.4336
2.500 1.1652 0.01302 0.00562 -0.1753 0.3926 0.4382
2.750 1.1932 0.01319 0.00575 -0.1751 0.3887 0.4421
3.000 1.2220 0.01328 0.00588 -0.1751 0.3857 0.4458
3.250 1.2503 0.01340 0.00603 -0.1751 0.3818 0.4500
3.500 1.2782 0.01355 0.00619 -0.1749 0.3778 0.4553
3.750 1.3057 0.01373 0.00635 -0.1747 0.3739 0.4613
4.000 1.3328 0.01393 0.00652 -0.1745 0.3701 0.4664
4.250 1.3608 0.01405 0.00670 -0.1744 0.3662 0.4712
4.500 1.3882 0.01421 0.00689 -0.1742 0.3611 0.4755
4.750 1.4147 0.01441 0.00708 -0.1739 0.3556 0.4796
5.000 1.4412 0.01462 0.00727 -0.1735 0.3507 0.4831
5.250 1.4681 0.01479 0.00745 -0.1733 0.3450 0.4858
5.500 1.4938 0.01502 0.00766 -0.1729 0.3378 0.4884
5.750 1.5192 0.01525 0.00790 -0.1724 0.3300 0.4915
6.000 1.5428 0.01558 0.00820 -0.1717 0.3175 0.4948
6.250 1.5651 0.01600 0.00854 -0.1707 0.3001 0.4980
6.500 1.5843 0.01659 0.00901 -0.1694 0.2766 0.5008
6.750 1.6011 0.01732 0.00959 -0.1677 0.2549 0.5036
7.000 1.6176 0.01802 0.01020 -0.1659 0.2385 0.5062
7.250 1.6342 0.01865 0.01077 -0.1641 0.2267 0.5089
7.500 1.6494 0.01928 0.01137 -0.1621 0.2175 0.5118
7.750 1.6619 0.01990 0.01198 -0.1596 0.2096 0.5147
8.000 1.6725 0.02057 0.01266 -0.1569 0.2033 0.5173
8.250 1.6862 0.02124 0.01335 -0.1548 0.1975 0.5201
8.500 1.6975 0.02209 0.01420 -0.1525 0.1918 0.5228
8.750 1.7109 0.02287 0.01500 -0.1506 0.1873 0.5258
9.000 1.7236 0.02371 0.01586 -0.1487 0.1829 0.5290
9.250 1.7345 0.02471 0.01688 -0.1468 0.1790 0.5319
9.500 1.7444 0.02584 0.01804 -0.1450 0.1755 0.5347
9.750 1.7570 0.02684 0.01910 -0.1435 0.1727 0.5376
10.000 1.7682 0.02799 0.02031 -0.1420 0.1699 0.5406
10.250 1.7778 0.02931 0.02168 -0.1405 0.1671 0.5436
10.500 1.7853 0.03086 0.02328 -0.1390 0.1645 0.5466
10.750 1.7915 0.03261 0.02507 -0.1376 0.1621 0.5498
11.000 1.8010 0.03413 0.02666 -0.1365 0.1603 0.5532
11.500 1.8151 0.03776 0.03043 -0.1344 0.1561 0.5595
11.750 1.8193 0.03994 0.03269 -0.1334 0.1540 0.5625
12.000 1.8209 0.04245 0.03526 -0.1324 0.1518 0.5655
12.250 1.8199 0.04527 0.03814 -0.1315 0.1496 0.5685
12.500 1.8234 0.04765 0.04061 -0.1308 0.1479 0.5718
12.750 1.8259 0.05019 0.04322 -0.1301 0.1462 0.5750
13.000 1.8268 0.05296 0.04607 -0.1295 0.1445 0.5779
13.250 1.8265 0.05590 0.04910 -0.1289 0.1428 0.5808
13.500 1.8247 0.05904 0.05233 -0.1284 0.1412 0.5839
13.750 1.8214 0.06241 0.05577 -0.1279 0.1396 0.5873
14.000 1.8162 0.06608 0.05951 -0.1276 0.1379 0.5906
14.250 1.8144 0.06934 0.06285 -0.1273 0.1365 0.5941
14.500 1.8154 0.07226 0.06585 -0.1270 0.1350 0.5976
14.750 1.8142 0.07551 0.06918 -0.1268 0.1334 0.6006
15.000 1.8138 0.07865 0.07240 -0.1267 0.1318 0.6034
15.250 1.8108 0.08215 0.07598 -0.1266 0.1301 0.6064
15.500 1.8077 0.08564 0.07954 -0.1265 0.1283 0.6095
15.750 1.8019 0.08956 0.08351 -0.1267 0.1265 0.6126
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