GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 675 AIRFOIL (goe675-il) Reynolds number: 100,000 Max Cl/Cd: 51.19 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe675-il-100000.txt Download as CSV file: xf-goe675-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 675 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2538 0.10862 0.10389 -0.0488 0.9580 0.1312
-7.250 -0.2774 0.10762 0.10294 -0.0505 0.9506 0.1350
-7.000 -0.3105 0.10465 0.10000 -0.0600 0.9409 0.1369
-6.750 -0.2746 0.10104 0.09640 -0.0542 0.9398 0.1389
-6.500 -0.2630 0.09896 0.09433 -0.0524 0.9345 0.1415
-6.250 -0.2614 0.09687 0.09226 -0.0522 0.9279 0.1446
-6.000 -0.2722 0.09178 0.08702 -0.0690 0.9182 0.1529
-5.750 -0.2646 0.08914 0.08446 -0.0644 0.9121 0.1540
-5.500 -0.2368 0.08636 0.08169 -0.0635 0.9067 0.1567
-5.250 -0.2249 0.08222 0.07719 -0.0777 0.8940 0.1697
-5.000 -0.1981 0.07816 0.07328 -0.0754 0.8885 0.1717
-4.750 -0.1735 0.07610 0.07126 -0.0740 0.8818 0.1762
-4.500 -0.1574 0.07210 0.06705 -0.0811 0.8722 0.1894
-4.250 -0.1060 0.05635 0.05032 -0.0988 0.8691 0.1387
-4.000 -0.0852 0.05513 0.04912 -0.0985 0.8619 0.1418
-3.750 -0.0432 0.04681 0.03954 -0.1059 0.8565 0.1351
-3.500 -0.0053 0.04527 0.03802 -0.1084 0.8514 0.1421
-3.250 0.0473 0.04289 0.03489 -0.1132 0.8484 0.1519
-3.000 0.0562 0.04212 0.03420 -0.1110 0.8374 0.1561
-2.750 0.0984 0.04115 0.03307 -0.1135 0.8326 0.1654
-2.500 0.1298 0.04005 0.03162 -0.1146 0.8256 0.1718
-2.250 0.1579 0.03946 0.03108 -0.1148 0.8174 0.1776
-2.000 0.2052 0.03821 0.02953 -0.1178 0.8135 0.1838
-1.750 0.2249 0.03804 0.02908 -0.1166 0.8029 0.1870
-1.500 0.2663 0.03675 0.02774 -0.1187 0.7977 0.1915
-1.250 0.3148 0.03561 0.02653 -0.1214 0.7946 0.1984
-1.000 0.3299 0.03564 0.02646 -0.1195 0.7820 0.2019
-0.750 0.3760 0.03442 0.02515 -0.1217 0.7783 0.2083
-0.500 0.4270 0.03316 0.02393 -0.1246 0.7762 0.2187
-0.250 0.4395 0.03330 0.02400 -0.1220 0.7621 0.2248
0.000 0.4893 0.03185 0.02269 -0.1246 0.7598 0.2392
0.250 0.5050 0.03184 0.02277 -0.1225 0.7466 0.2515
0.500 0.5532 0.03038 0.02145 -0.1247 0.7439 0.2852
0.750 0.6030 0.02848 0.02003 -0.1271 0.7419 0.3737
1.000 0.6188 0.02684 0.02009 -0.1238 0.7295 1.0000
1.250 0.6665 0.02579 0.01870 -0.1258 0.7260 1.0000
1.500 0.7169 0.02463 0.01731 -0.1283 0.7235 1.0000
1.750 0.7350 0.02471 0.01729 -0.1262 0.7095 1.0000
2.000 0.7858 0.02350 0.01590 -0.1288 0.7062 1.0000
2.500 0.8382 0.02316 0.01537 -0.1272 0.6824 1.0000
2.750 0.8781 0.02248 0.01455 -0.1283 0.6738 1.0000
3.000 0.9049 0.02239 0.01438 -0.1277 0.6614 1.0000
3.250 0.9504 0.02164 0.01346 -0.1299 0.6539 1.0000
3.500 0.9717 0.02187 0.01363 -0.1285 0.6401 1.0000
3.750 0.9997 0.02192 0.01359 -0.1282 0.6284 1.0000
4.000 1.0383 0.02163 0.01313 -0.1296 0.6191 1.0000
4.250 1.0576 0.02208 0.01355 -0.1281 0.6063 1.0000
4.500 1.0878 0.02222 0.01359 -0.1283 0.5965 1.0000
4.750 1.1154 0.02244 0.01373 -0.1281 0.5861 1.0000
5.000 1.1379 0.02289 0.01415 -0.1272 0.5759 1.0000
5.250 1.1701 0.02305 0.01418 -0.1278 0.5672 1.0000
5.500 1.1888 0.02367 0.01484 -0.1263 0.5574 1.0000
5.750 1.2215 0.02386 0.01491 -0.1270 0.5494 1.0000
6.000 1.2387 0.02456 0.01566 -0.1254 0.5403 1.0000
6.250 1.2693 0.02486 0.01588 -0.1259 0.5325 1.0000
6.500 1.2882 0.02556 0.01662 -0.1246 0.5242 1.0000
6.750 1.3145 0.02599 0.01702 -0.1243 0.5163 1.0000
7.000 1.3386 0.02659 0.01762 -0.1238 0.5089 1.0000
7.250 1.3578 0.02724 0.01831 -0.1226 0.5007 1.0000
7.500 1.3914 0.02761 0.01857 -0.1236 0.4939 1.0000
7.750 1.4011 0.02855 0.01968 -0.1209 0.4857 1.0000
8.000 1.4354 0.02889 0.01991 -0.1220 0.4788 1.0000
8.250 1.4465 0.02990 0.02107 -0.1196 0.4714 1.0000
8.500 1.4687 0.03055 0.02175 -0.1189 0.4642 1.0000
8.750 1.4978 0.03116 0.02233 -0.1192 0.4575 1.0000
9.000 1.5047 0.03222 0.02356 -0.1162 0.4497 1.0000
9.250 1.5476 0.03235 0.02351 -0.1185 0.4419 1.0000
9.500 1.5425 0.03365 0.02508 -0.1138 0.4340 1.0000
9.750 1.5777 0.03376 0.02505 -0.1148 0.4251 1.0000
10.000 1.5783 0.03495 0.02644 -0.1109 0.4173 1.0000
10.250 1.6022 0.03530 0.02677 -0.1103 0.4087 1.0000
10.500 1.6124 0.03622 0.02778 -0.1079 0.4009 1.0000
10.750 1.6209 0.03699 0.02864 -0.1051 0.3930 1.0000
11.000 1.6468 0.03741 0.02903 -0.1050 0.3851 1.0000
11.250 1.6356 0.03865 0.03048 -0.0994 0.3779 1.0000
11.500 1.6713 0.03841 0.03009 -0.1004 0.3686 1.0000
11.750 1.6485 0.04007 0.03202 -0.0936 0.3618 1.0000
12.000 1.6880 0.03943 0.03116 -0.0949 0.3522 1.0000
12.250 1.6584 0.04162 0.03368 -0.0879 0.3461 1.0000
12.500 1.6687 0.04215 0.03426 -0.0858 0.3384 1.0000
12.750 1.6697 0.04330 0.03549 -0.0828 0.3313 1.0000
13.000 1.6612 0.04490 0.03725 -0.0791 0.3239 1.0000
13.250 1.6750 0.04524 0.03757 -0.0775 0.3161 1.0000
13.500 1.6556 0.04777 0.04032 -0.0734 0.3090 1.0000
13.750 1.6708 0.04788 0.04037 -0.0720 0.3005 1.0000
14.000 1.6473 0.05110 0.04384 -0.0683 0.2933 1.0000
14.250 1.6623 0.05128 0.04395 -0.0670 0.2850 1.0000
14.500 1.6358 0.05522 0.04818 -0.0639 0.2779 1.0000
14.750 1.6469 0.05576 0.04866 -0.0626 0.2694 1.0000
15.000 1.6197 0.06032 0.05349 -0.0602 0.2619 1.0000
15.250 1.6222 0.06190 0.05506 -0.0590 0.2529 1.0000
15.500 1.5989 0.06667 0.06006 -0.0577 0.2445 1.0000
15.750 1.5889 0.07007 0.06353 -0.0568 0.2350 1.0000
16.000 1.5818 0.07321 0.06666 -0.0562 0.2238 1.0000
16.250 1.5531 0.07966 0.07333 -0.0563 0.2141 1.0000
16.500 1.5335 0.08507 0.07882 -0.0566 0.2021 1.0000
16.750 1.5126 0.09091 0.08468 -0.0573 0.1886 1.0000
17.000 1.4897 0.09726 0.09102 -0.0584 0.1735 1.0000
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Polar data table (+)
Polar graphs
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