GOE 567 AIRFOIL (goe567-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 567 AIRFOIL (goe567-il) Reynolds number: 100,000 Max Cl/Cd: 49.7 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe567-il-100000.txt Download as CSV file: xf-goe567-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 567 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3076 0.12056 0.11592 -0.0336 1.0000 0.1489
-9.750 -0.3299 0.12081 0.11627 -0.0307 1.0000 0.1523
-9.500 -0.3377 0.11699 0.11248 -0.0387 0.9942 0.1567
-9.250 -0.2930 0.11267 0.10808 -0.0389 0.9910 0.1628
-9.000 -0.3244 0.11095 0.10644 -0.0525 0.9792 0.1715
-8.750 -0.2629 0.10474 0.10009 -0.0494 0.9790 0.1755
-8.500 -0.2474 0.10185 0.09717 -0.0544 0.9719 0.1853
-8.250 -0.2370 0.09765 0.09297 -0.0591 0.9648 0.1901
-8.000 -0.2049 0.09430 0.08955 -0.0610 0.9594 0.1958
-7.750 -0.2356 0.09216 0.08750 -0.0690 0.9445 0.2047
-7.500 -0.1750 0.08778 0.08299 -0.0683 0.9446 0.2104
-7.250 -0.3160 0.05641 0.05121 -0.1061 0.9143 0.1408
-7.000 -0.2932 0.04947 0.04389 -0.1133 0.9088 0.1381
-6.750 -0.2839 0.04434 0.03828 -0.1167 0.8992 0.1381
-6.500 -0.2530 0.03954 0.03270 -0.1223 0.8936 0.1396
-6.250 -0.2115 0.03605 0.02885 -0.1271 0.8908 0.1420
-6.000 -0.1986 0.03527 0.02806 -0.1253 0.8803 0.1445
-5.750 -0.1568 0.03345 0.02598 -0.1287 0.8765 0.1489
-5.500 -0.1267 0.03187 0.02400 -0.1301 0.8701 0.1519
-5.250 -0.0964 0.03071 0.02235 -0.1312 0.8629 0.1556
-5.000 -0.0521 0.02915 0.02085 -0.1344 0.8598 0.1611
-4.750 -0.0211 0.02834 0.01986 -0.1352 0.8536 0.1658
-4.500 0.0084 0.02765 0.01888 -0.1356 0.8462 0.1711
-4.250 0.0505 0.02651 0.01785 -0.1381 0.8428 0.1788
-4.000 0.0747 0.02617 0.01735 -0.1375 0.8348 0.1857
-3.750 0.1076 0.02543 0.01669 -0.1383 0.8288 0.1941
-3.500 0.1494 0.02455 0.01581 -0.1405 0.8253 0.2089
-3.250 0.1679 0.02448 0.01577 -0.1390 0.8159 0.2229
-3.000 0.2034 0.02380 0.01524 -0.1402 0.8108 0.2519
-2.750 0.2434 0.02313 0.01487 -0.1418 0.8073 0.3109
-2.500 0.2574 0.02365 0.01552 -0.1396 0.7967 0.3517
-2.250 0.2940 0.02358 0.01546 -0.1404 0.7922 0.3928
-2.000 0.3154 0.02402 0.01596 -0.1391 0.7843 0.4170
-1.750 0.3440 0.02420 0.01609 -0.1389 0.7775 0.4435
-1.500 0.3808 0.02405 0.01595 -0.1396 0.7736 0.4664
-1.250 0.3941 0.02470 0.01664 -0.1373 0.7635 0.4830
-1.000 0.4264 0.02470 0.01665 -0.1374 0.7586 0.5060
-0.750 0.4635 0.02454 0.01646 -0.1381 0.7552 0.5330
-0.500 0.4719 0.02535 0.01733 -0.1352 0.7441 0.5495
-0.250 0.5061 0.02510 0.01709 -0.1355 0.7400 0.5697
0.000 0.5200 0.02574 0.01776 -0.1336 0.7311 0.5849
0.250 0.5494 0.02565 0.01766 -0.1336 0.7255 0.6017
0.500 0.5860 0.02527 0.01725 -0.1344 0.7219 0.6197
0.750 0.5942 0.02619 0.01821 -0.1319 0.7117 0.6336
1.000 0.6264 0.02597 0.01799 -0.1322 0.7072 0.6513
1.250 0.6631 0.02556 0.01758 -0.1331 0.7040 0.6703
1.500 0.6660 0.02669 0.01881 -0.1299 0.6931 0.6850
1.750 0.6998 0.02635 0.01849 -0.1303 0.6892 0.7056
2.000 0.7161 0.02698 0.01920 -0.1288 0.6822 0.7253
2.250 0.7354 0.02736 0.01967 -0.1276 0.6751 0.7491
2.500 0.7709 0.02682 0.01923 -0.1281 0.6717 0.7825
2.750 0.7715 0.02792 0.02063 -0.1244 0.6627 0.8282
3.000 0.8082 0.02785 0.02067 -0.1261 0.6574 1.0000
3.250 0.8539 0.02756 0.02021 -0.1289 0.6543 1.0000
3.500 0.8530 0.02954 0.02221 -0.1261 0.6439 1.0000
3.750 0.8906 0.02938 0.02194 -0.1274 0.6397 1.0000
4.000 0.9379 0.02863 0.02108 -0.1295 0.6367 1.0000
4.250 0.9296 0.03082 0.02333 -0.1254 0.6253 1.0000
4.500 0.9761 0.02995 0.02237 -0.1273 0.6218 1.0000
4.750 0.9789 0.03155 0.02400 -0.1244 0.6126 1.0000
5.000 1.0146 0.03117 0.02360 -0.1249 0.6072 1.0000
5.250 1.0628 0.03018 0.02255 -0.1270 0.6040 1.0000
5.500 1.0529 0.03241 0.02487 -0.1225 0.5932 1.0000
5.750 1.0985 0.03148 0.02392 -0.1242 0.5893 1.0000
6.000 1.1450 0.03052 0.02292 -0.1259 0.5853 1.0000
6.250 1.1413 0.03220 0.02470 -0.1220 0.5748 1.0000
6.500 1.1999 0.03036 0.02279 -0.1250 0.5707 1.0000
6.750 1.1948 0.03208 0.02465 -0.1208 0.5605 1.0000
7.000 1.2471 0.03058 0.02310 -0.1231 0.5553 1.0000
7.250 1.2538 0.03161 0.02424 -0.1201 0.5462 1.0000
7.500 1.2968 0.03060 0.02321 -0.1214 0.5396 1.0000
7.750 1.3131 0.03098 0.02366 -0.1195 0.5307 1.0000
8.000 1.3559 0.02988 0.02254 -0.1206 0.5225 1.0000
8.250 1.3656 0.03055 0.02332 -0.1179 0.5132 1.0000
8.500 1.4062 0.02977 0.02253 -0.1190 0.5056 1.0000
8.750 1.4126 0.03055 0.02345 -0.1158 0.4961 1.0000
9.000 1.4587 0.02952 0.02236 -0.1176 0.4877 1.0000
9.250 1.4557 0.03058 0.02361 -0.1132 0.4776 1.0000
9.500 1.4870 0.03020 0.02326 -0.1131 0.4686 1.0000
9.750 1.4972 0.03054 0.02371 -0.1102 0.4581 1.0000
10.000 1.5032 0.03090 0.02417 -0.1067 0.4472 1.0000
10.250 1.5196 0.03072 0.02400 -0.1044 0.4350 1.0000
10.500 1.5316 0.03082 0.02414 -0.1016 0.4231 1.0000
10.750 1.5233 0.03189 0.02537 -0.0968 0.4115 1.0000
11.000 1.5245 0.03264 0.02620 -0.0933 0.3989 1.0000
11.250 1.5254 0.03348 0.02710 -0.0899 0.3849 1.0000
11.500 1.5216 0.03468 0.02836 -0.0865 0.3693 1.0000
11.750 1.5144 0.03630 0.03003 -0.0831 0.3519 1.0000
12.000 1.5065 0.03819 0.03194 -0.0801 0.3320 1.0000
12.250 1.4983 0.04033 0.03399 -0.0774 0.3097 1.0000
12.500 1.4847 0.04322 0.03683 -0.0748 0.2851 1.0000
12.750 1.4724 0.04627 0.03971 -0.0727 0.2605 1.0000
13.000 1.4601 0.04957 0.04282 -0.0708 0.2375 1.0000
13.250 1.4498 0.05290 0.04595 -0.0693 0.2174 1.0000
13.500 1.4409 0.05635 0.04928 -0.0681 0.1992 1.0000
13.750 1.4347 0.05964 0.05245 -0.0670 0.1831 1.0000
14.000 1.4322 0.06265 0.05533 -0.0661 0.1691 1.0000
14.250 1.4341 0.06522 0.05775 -0.0652 0.1570 1.0000
14.500 1.4410 0.06724 0.05955 -0.0643 0.1462 1.0000
14.750 1.4411 0.07023 0.06266 -0.0639 0.1377 1.0000
15.000 1.4486 0.07233 0.06466 -0.0632 0.1292 1.0000
15.250 1.4540 0.07471 0.06704 -0.0628 0.1220 1.0000
15.500 1.4640 0.07670 0.06904 -0.0621 0.1154 1.0000
15.750 1.4681 0.07936 0.07180 -0.0619 0.1097 1.0000
16.000 1.4812 0.08105 0.07343 -0.0613 0.1033 1.0000
16.250 1.4759 0.08487 0.07753 -0.0616 0.0988 1.0000
16.500 1.4890 0.08642 0.07888 -0.0611 0.0920 1.0000
16.750 1.4747 0.09147 0.08431 -0.0621 0.0884 1.0000
17.000 1.4702 0.09526 0.08822 -0.0628 0.0835 1.0000
17.250 1.4697 0.09866 0.09167 -0.0633 0.0787 1.0000
17.500 1.4627 0.10310 0.09631 -0.0644 0.0745 1.0000
17.750 1.4701 0.10527 0.09832 -0.0645 0.0699 1.0000
18.000 1.4607 0.11032 0.10368 -0.0660 0.0668 1.0000
18.250 1.4632 0.11335 0.10671 -0.0667 0.0635 1.0000
18.500 1.4712 0.11582 0.10919 -0.0667 0.0603 1.0000
18.750 1.4602 0.12135 0.11503 -0.0687 0.0589 1.0000
19.000 1.4502 0.12678 0.12072 -0.0709 0.0575 1.0000
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Polar data table (+)
Polar graphs
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