GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 675 AIRFOIL (goe675-il) Reynolds number: 500,000 Max Cl/Cd: 104.38 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe675-il-500000.txt Download as CSV file: xf-goe675-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6090 0.03706 0.03337 -0.1456 0.9411 0.0370
-12.750 -0.6205 0.03313 0.02913 -0.1476 0.9318 0.0371
-12.500 -0.6168 0.03054 0.02634 -0.1480 0.9253 0.0374
-12.250 -0.6054 0.02876 0.02440 -0.1479 0.9203 0.0377
-12.000 -0.5901 0.02732 0.02286 -0.1477 0.9152 0.0380
-11.750 -0.5727 0.02607 0.02149 -0.1475 0.9105 0.0383
-11.500 -0.5542 0.02490 0.02018 -0.1472 0.9064 0.0386
-11.250 -0.5344 0.02384 0.01897 -0.1469 0.9025 0.0390
-11.000 -0.5137 0.02279 0.01780 -0.1467 0.8984 0.0395
-10.750 -0.4920 0.02184 0.01670 -0.1464 0.8942 0.0400
-10.500 -0.4694 0.02097 0.01567 -0.1461 0.8904 0.0405
-10.250 -0.4460 0.02018 0.01471 -0.1458 0.8871 0.0410
-10.000 -0.4219 0.01949 0.01386 -0.1455 0.8837 0.0414
-9.750 -0.3994 0.01845 0.01276 -0.1452 0.8798 0.0420
-9.500 -0.3749 0.01777 0.01204 -0.1449 0.8759 0.0426
-9.250 -0.3493 0.01723 0.01145 -0.1447 0.8725 0.0433
-9.000 -0.3232 0.01673 0.01087 -0.1446 0.8695 0.0440
-8.750 -0.2969 0.01628 0.01032 -0.1444 0.8663 0.0449
-8.500 -0.2707 0.01580 0.00976 -0.1442 0.8627 0.0457
-8.250 -0.2446 0.01526 0.00916 -0.1440 0.8589 0.0467
-8.000 -0.2179 0.01482 0.00872 -0.1439 0.8555 0.0479
-7.750 -0.1903 0.01450 0.00835 -0.1438 0.8524 0.0494
-7.500 -0.1625 0.01420 0.00796 -0.1437 0.8492 0.0511
-7.250 -0.1355 0.01386 0.00763 -0.1436 0.8451 0.0531
-7.000 -0.1078 0.01364 0.00739 -0.1435 0.8404 0.0554
-6.750 -0.0798 0.01334 0.00704 -0.1434 0.8361 0.0583
-6.500 -0.0510 0.01323 0.00690 -0.1434 0.8324 0.0617
-6.250 -0.0225 0.01311 0.00675 -0.1433 0.8286 0.0657
-6.000 0.0060 0.01310 0.00672 -0.1433 0.8241 0.0699
-5.750 0.0343 0.01294 0.00656 -0.1433 0.8195 0.0734
-5.500 0.0634 0.01293 0.00650 -0.1433 0.8156 0.0769
-5.250 0.0923 0.01278 0.00626 -0.1434 0.8118 0.0802
-5.000 0.1201 0.01267 0.00620 -0.1434 0.8070 0.0829
-4.750 0.1486 0.01259 0.00608 -0.1433 0.8021 0.0858
-4.500 0.1775 0.01253 0.00592 -0.1433 0.7974 0.0878
-4.250 0.2055 0.01211 0.00550 -0.1433 0.7928 0.0905
-4.000 0.2333 0.01196 0.00538 -0.1433 0.7874 0.0928
-3.750 0.2618 0.01184 0.00523 -0.1433 0.7827 0.0951
-3.500 0.2908 0.01174 0.00506 -0.1433 0.7784 0.0972
-3.250 0.3189 0.01146 0.00477 -0.1433 0.7737 0.0997
-3.000 0.3467 0.01128 0.00463 -0.1432 0.7680 0.1024
-2.750 0.3752 0.01117 0.00451 -0.1432 0.7628 0.1051
-2.500 0.4045 0.01111 0.00438 -0.1433 0.7582 0.1079
-2.250 0.4323 0.01102 0.00429 -0.1432 0.7522 0.1094
-2.000 0.4598 0.01068 0.00396 -0.1431 0.7462 0.1119
-1.750 0.4884 0.01052 0.00377 -0.1431 0.7406 0.1142
-1.500 0.5160 0.01040 0.00369 -0.1430 0.7338 0.1167
-1.250 0.5441 0.01031 0.00357 -0.1429 0.7273 0.1195
-1.000 0.5724 0.01024 0.00346 -0.1428 0.7208 0.1219
-0.750 0.5997 0.01006 0.00332 -0.1426 0.7128 0.1266
-0.500 0.6277 0.00999 0.00322 -0.1425 0.7054 0.1318
-0.250 0.6550 0.00991 0.00316 -0.1423 0.6968 0.1382
0.000 0.6825 0.00983 0.00308 -0.1421 0.6885 0.1498
0.250 0.7095 0.00972 0.00305 -0.1419 0.6787 0.1687
0.500 0.7362 0.00960 0.00302 -0.1417 0.6686 0.2063
0.750 0.7623 0.00947 0.00308 -0.1414 0.6569 0.2739
1.000 0.7885 0.00940 0.00312 -0.1410 0.6450 0.3286
1.250 0.8138 0.00931 0.00318 -0.1406 0.6319 0.3996
1.500 0.8374 0.00904 0.00330 -0.1399 0.6168 0.5616
1.750 0.8662 0.00832 0.00349 -0.1397 0.5993 1.0000
2.000 0.8893 0.00852 0.00357 -0.1387 0.5799 1.0000
2.250 0.9118 0.00876 0.00368 -0.1376 0.5587 1.0000
2.500 0.9330 0.00905 0.00382 -0.1363 0.5358 1.0000
2.750 0.9533 0.00939 0.00399 -0.1348 0.5138 1.0000
3.000 0.9739 0.00973 0.00419 -0.1334 0.4948 1.0000
3.250 0.9953 0.01004 0.00439 -0.1322 0.4796 1.0000
3.500 1.0175 0.01032 0.00459 -0.1312 0.4677 1.0000
3.750 1.0389 0.01064 0.00482 -0.1300 0.4575 1.0000
4.000 1.0615 0.01091 0.00503 -0.1290 0.4485 1.0000
4.250 1.0827 0.01123 0.00527 -0.1278 0.4407 1.0000
4.500 1.1060 0.01146 0.00548 -0.1270 0.4341 1.0000
4.750 1.1266 0.01176 0.00572 -0.1257 0.4275 1.0000
5.000 1.1473 0.01205 0.00597 -0.1245 0.4216 1.0000
5.250 1.1694 0.01228 0.00620 -0.1234 0.4158 1.0000
5.500 1.1893 0.01262 0.00649 -0.1221 0.4091 1.0000
5.750 1.2101 0.01293 0.00677 -0.1209 0.4026 1.0000
6.000 1.2315 0.01319 0.00704 -0.1199 0.3960 1.0000
6.250 1.2511 0.01357 0.00736 -0.1186 0.3900 1.0000
6.500 1.2725 0.01388 0.00767 -0.1176 0.3849 1.0000
6.750 1.2942 0.01415 0.00797 -0.1167 0.3796 1.0000
7.000 1.3142 0.01452 0.00831 -0.1155 0.3740 1.0000
7.250 1.3338 0.01493 0.00870 -0.1143 0.3687 1.0000
7.500 1.3555 0.01520 0.00902 -0.1135 0.3637 1.0000
7.750 1.3757 0.01557 0.00940 -0.1124 0.3584 1.0000
8.000 1.3940 0.01606 0.00984 -0.1111 0.3533 1.0000
8.250 1.4149 0.01640 0.01023 -0.1102 0.3484 1.0000
8.500 1.4345 0.01679 0.01065 -0.1092 0.3422 1.0000
8.750 1.4502 0.01740 0.01120 -0.1076 0.3351 1.0000
9.000 1.4708 0.01776 0.01163 -0.1068 0.3283 1.0000
9.250 1.4880 0.01831 0.01217 -0.1055 0.3217 1.0000
9.500 1.5055 0.01886 0.01273 -0.1043 0.3157 1.0000
9.750 1.5239 0.01938 0.01328 -0.1032 0.3086 1.0000
10.000 1.5383 0.02011 0.01399 -0.1017 0.3014 1.0000
10.250 1.5567 0.02065 0.01457 -0.1007 0.2937 1.0000
10.500 1.5697 0.02149 0.01538 -0.0991 0.2848 1.0000
10.750 1.5856 0.02219 0.01610 -0.0978 0.2752 1.0000
11.000 1.5988 0.02306 0.01696 -0.0963 0.2657 1.0000
11.250 1.6097 0.02410 0.01796 -0.0946 0.2547 1.0000
11.500 1.6221 0.02506 0.01892 -0.0931 0.2429 1.0000
11.750 1.6315 0.02624 0.02006 -0.0914 0.2298 1.0000
12.000 1.6387 0.02759 0.02136 -0.0895 0.2153 1.0000
12.250 1.6444 0.02909 0.02280 -0.0875 0.2001 1.0000
12.500 1.6468 0.03088 0.02451 -0.0853 0.1834 1.0000
12.750 1.6461 0.03298 0.02651 -0.0831 0.1649 1.0000
13.000 1.6441 0.03526 0.02870 -0.0808 0.1451 1.0000
13.250 1.6378 0.03799 0.03130 -0.0784 0.1224 1.0000
13.500 1.6246 0.04147 0.03461 -0.0759 0.0960 1.0000
13.750 1.6111 0.04515 0.03818 -0.0736 0.0763 1.0000
14.000 1.6005 0.04872 0.04170 -0.0718 0.0605 1.0000
14.250 1.5930 0.05215 0.04510 -0.0704 0.0507 1.0000
14.500 1.5888 0.05534 0.04832 -0.0693 0.0466 1.0000
14.750 1.5862 0.05843 0.05146 -0.0685 0.0444 1.0000
15.000 1.5821 0.06179 0.05488 -0.0677 0.0428 1.0000
15.250 1.5793 0.06509 0.05826 -0.0672 0.0417 1.0000
15.500 1.5767 0.06843 0.06170 -0.0668 0.0409 1.0000
15.750 1.5723 0.07203 0.06539 -0.0665 0.0401 1.0000
16.000 1.5663 0.07592 0.06937 -0.0663 0.0394 1.0000
16.250 1.5585 0.08012 0.07367 -0.0663 0.0388 1.0000
16.500 1.5490 0.08464 0.07829 -0.0665 0.0382 1.0000
16.750 1.5380 0.08943 0.08317 -0.0669 0.0377 1.0000
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