GOE 567 AIRFOIL (goe567-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 567 AIRFOIL (goe567-il) Reynolds number: 500,000 Max Cl/Cd: 95.83 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe567-il-500000-n5.txt Download as CSV file: xf-goe567-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.5932 0.10333 0.10054 -0.0647 1.0000 0.0241
-15.500 -0.7139 0.07966 0.07656 -0.0781 1.0000 0.0230
-15.250 -0.7703 0.06824 0.06497 -0.0846 1.0000 0.0223
-15.000 -0.8125 0.05990 0.05648 -0.0890 1.0000 0.0220
-14.750 -0.8503 0.05294 0.04941 -0.0921 1.0000 0.0217
-14.500 -0.8857 0.04690 0.04326 -0.0944 0.9998 0.0215
-14.250 -0.8923 0.03988 0.03608 -0.1037 0.9939 0.0221
-14.000 -0.8958 0.03384 0.02990 -0.1122 0.9847 0.0232
-13.750 -0.8843 0.02888 0.02478 -0.1211 0.9752 0.0246
-13.500 -0.8568 0.02540 0.02111 -0.1291 0.9703 0.0266
-13.250 -0.8343 0.02372 0.01933 -0.1317 0.9624 0.0288
-13.000 -0.8025 0.02239 0.01788 -0.1351 0.9584 0.0309
-12.750 -0.7764 0.02135 0.01677 -0.1367 0.9509 0.0327
-12.500 -0.7449 0.02046 0.01578 -0.1389 0.9447 0.0349
-12.250 -0.7157 0.01965 0.01489 -0.1405 0.9361 0.0366
-12.000 -0.6833 0.01899 0.01416 -0.1425 0.9275 0.0387
-11.750 -0.6544 0.01839 0.01343 -0.1435 0.9154 0.0404
-11.500 -0.6254 0.01780 0.01273 -0.1445 0.9016 0.0418
-11.250 -0.5972 0.01732 0.01217 -0.1452 0.8857 0.0433
-11.000 -0.5702 0.01695 0.01168 -0.1455 0.8686 0.0449
-10.750 -0.5445 0.01660 0.01118 -0.1454 0.8510 0.0464
-10.500 -0.5194 0.01628 0.01069 -0.1452 0.8346 0.0476
-10.250 -0.4950 0.01591 0.01021 -0.1450 0.8195 0.0489
-10.000 -0.4698 0.01565 0.00987 -0.1448 0.8065 0.0503
-9.500 -0.4179 0.01529 0.00931 -0.1444 0.7849 0.0537
-9.250 -0.3918 0.01512 0.00901 -0.1442 0.7762 0.0551
-9.000 -0.3663 0.01475 0.00856 -0.1440 0.7677 0.0564
-8.750 -0.3408 0.01442 0.00816 -0.1438 0.7601 0.0575
-8.500 -0.3144 0.01415 0.00783 -0.1437 0.7531 0.0586
-8.250 -0.2879 0.01391 0.00751 -0.1436 0.7463 0.0597
-8.000 -0.2612 0.01367 0.00720 -0.1435 0.7405 0.0609
-7.750 -0.2342 0.01344 0.00690 -0.1434 0.7343 0.0622
-7.500 -0.2073 0.01325 0.00661 -0.1433 0.7285 0.0634
-7.250 -0.1801 0.01305 0.00633 -0.1432 0.7234 0.0643
-7.000 -0.1532 0.01273 0.00596 -0.1431 0.7180 0.0654
-6.750 -0.1264 0.01244 0.00562 -0.1431 0.7126 0.0669
-6.500 -0.0991 0.01224 0.00536 -0.1430 0.7076 0.0683
-6.250 -0.0714 0.01204 0.00514 -0.1430 0.7027 0.0698
-6.000 -0.0438 0.01188 0.00492 -0.1430 0.6976 0.0714
-5.750 -0.0163 0.01173 0.00469 -0.1429 0.6926 0.0728
-5.500 0.0116 0.01156 0.00448 -0.1429 0.6878 0.0740
-5.250 0.0395 0.01142 0.00429 -0.1429 0.6828 0.0750
-5.000 0.0670 0.01123 0.00404 -0.1428 0.6778 0.0767
-4.750 0.0947 0.01102 0.00381 -0.1428 0.6729 0.0790
-4.500 0.1226 0.01085 0.00362 -0.1428 0.6677 0.0810
-4.250 0.1505 0.01072 0.00346 -0.1428 0.6625 0.0828
-4.000 0.1783 0.01063 0.00330 -0.1427 0.6576 0.0846
-3.750 0.2066 0.01051 0.00316 -0.1428 0.6522 0.0866
-3.500 0.2345 0.01042 0.00303 -0.1427 0.6463 0.0885
-3.000 0.2904 0.01018 0.00277 -0.1427 0.6358 0.0958
-2.750 0.3182 0.01010 0.00266 -0.1426 0.6290 0.0998
-2.500 0.3458 0.01000 0.00256 -0.1425 0.6214 0.1081
-2.250 0.3733 0.00987 0.00246 -0.1424 0.6128 0.1254
-2.000 0.4006 0.00972 0.00238 -0.1424 0.6048 0.1560
-1.750 0.4281 0.00959 0.00232 -0.1423 0.5972 0.1870
-1.500 0.4554 0.00951 0.00228 -0.1422 0.5902 0.2134
-1.250 0.4831 0.00943 0.00226 -0.1422 0.5829 0.2390
-1.000 0.5104 0.00939 0.00226 -0.1421 0.5765 0.2647
-0.750 0.5381 0.00935 0.00227 -0.1420 0.5701 0.2900
-0.500 0.5654 0.00934 0.00229 -0.1418 0.5628 0.3132
-0.250 0.5927 0.00935 0.00233 -0.1417 0.5566 0.3356
0.000 0.6202 0.00937 0.00237 -0.1416 0.5497 0.3528
0.250 0.6472 0.00943 0.00242 -0.1413 0.5438 0.3660
0.500 0.6746 0.00947 0.00247 -0.1412 0.5367 0.3803
0.750 0.7012 0.00954 0.00254 -0.1409 0.5287 0.3956
1.000 0.7282 0.00959 0.00262 -0.1407 0.5218 0.4114
1.250 0.7553 0.00965 0.00270 -0.1404 0.5156 0.4241
1.750 0.8091 0.00981 0.00286 -0.1400 0.5045 0.4450
2.000 0.8357 0.00989 0.00296 -0.1397 0.4980 0.4576
2.250 0.8619 0.00999 0.00307 -0.1393 0.4910 0.4704
2.500 0.8879 0.01010 0.00318 -0.1389 0.4815 0.4818
2.750 0.9135 0.01022 0.00329 -0.1384 0.4720 0.4917
3.000 0.9389 0.01036 0.00341 -0.1380 0.4628 0.5016
3.250 0.9649 0.01046 0.00354 -0.1376 0.4560 0.5114
3.500 0.9903 0.01059 0.00367 -0.1371 0.4478 0.5214
3.750 1.0154 0.01073 0.00382 -0.1366 0.4390 0.5317
4.000 1.0393 0.01091 0.00398 -0.1358 0.4272 0.5417
4.250 1.0629 0.01111 0.00415 -0.1350 0.4131 0.5527
4.500 1.0857 0.01133 0.00435 -0.1341 0.3978 0.5637
4.750 1.1078 0.01158 0.00457 -0.1331 0.3814 0.5752
5.250 1.1500 0.01215 0.00507 -0.1307 0.3478 0.6020
5.500 1.1693 0.01250 0.00537 -0.1292 0.3265 0.6176
5.750 1.1863 0.01292 0.00573 -0.1274 0.3029 0.6367
6.000 1.2003 0.01338 0.00614 -0.1250 0.2764 0.6609
6.250 1.2117 0.01385 0.00661 -0.1222 0.2514 0.6998
6.500 1.2220 0.01402 0.00712 -0.1190 0.2257 1.0000
6.750 1.2307 0.01480 0.00774 -0.1159 0.1962 1.0000
7.000 1.2250 0.01625 0.00883 -0.1108 0.1358 1.0000
7.250 1.2363 0.01696 0.00947 -0.1084 0.1232 1.0000
7.500 1.2518 0.01748 0.00999 -0.1066 0.1187 1.0000
7.750 1.2668 0.01804 0.01055 -0.1048 0.1147 1.0000
8.000 1.2806 0.01867 0.01118 -0.1029 0.1104 1.0000
8.250 1.2957 0.01927 0.01179 -0.1013 0.1074 1.0000
8.500 1.3113 0.01984 0.01240 -0.0998 0.1049 1.0000
8.750 1.3263 0.02048 0.01307 -0.0982 0.1026 1.0000
9.000 1.3392 0.02125 0.01386 -0.0965 0.0989 1.0000
9.250 1.3503 0.02217 0.01478 -0.0947 0.0948 1.0000
9.500 1.3647 0.02291 0.01557 -0.0933 0.0906 1.0000
10.000 1.3762 0.02567 0.01817 -0.0892 0.0615 1.0000
10.250 1.3827 0.02710 0.01959 -0.0875 0.0573 1.0000
10.500 1.3921 0.02837 0.02090 -0.0861 0.0550 1.0000
10.750 1.4018 0.02967 0.02225 -0.0848 0.0538 1.0000
11.000 1.4108 0.03106 0.02369 -0.0835 0.0526 1.0000
11.250 1.4188 0.03258 0.02526 -0.0823 0.0515 1.0000
11.500 1.4263 0.03417 0.02691 -0.0811 0.0506 1.0000
11.750 1.4321 0.03597 0.02875 -0.0799 0.0492 1.0000
12.000 1.4378 0.03781 0.03065 -0.0789 0.0481 1.0000
12.250 1.4448 0.03960 0.03250 -0.0779 0.0474 1.0000
12.500 1.4537 0.04123 0.03421 -0.0772 0.0466 1.0000
12.750 1.4615 0.04300 0.03605 -0.0764 0.0458 1.0000
13.000 1.4684 0.04491 0.03803 -0.0757 0.0448 1.0000
13.250 1.4745 0.04694 0.04012 -0.0751 0.0437 1.0000
13.500 1.4797 0.04912 0.04236 -0.0745 0.0427 1.0000
13.750 1.4834 0.05149 0.04480 -0.0739 0.0418 1.0000
14.000 1.4855 0.05413 0.04749 -0.0735 0.0405 1.0000
14.250 1.4929 0.05620 0.04964 -0.0732 0.0396 1.0000
14.500 1.5005 0.05829 0.05181 -0.0729 0.0382 1.0000
14.750 1.5066 0.06059 0.05417 -0.0727 0.0364 1.0000
15.000 1.5103 0.06320 0.05680 -0.0726 0.0343 1.0000
15.250 1.5167 0.06555 0.05923 -0.0726 0.0315 1.0000
15.500 1.5198 0.06832 0.06200 -0.0726 0.0246 1.0000
16.000 1.5120 0.07587 0.06951 -0.0731 0.0158 1.0000
16.250 1.5097 0.07957 0.07327 -0.0735 0.0146 1.0000
16.500 1.5096 0.08301 0.07679 -0.0739 0.0138 1.0000
16.750 1.5096 0.08648 0.08034 -0.0744 0.0132 1.0000
17.000 1.5089 0.09010 0.08405 -0.0751 0.0127 1.0000
17.250 1.5078 0.09381 0.08783 -0.0758 0.0122 1.0000
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Polar data table (+)
Polar graphs
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