GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 675 AIRFOIL (goe675-il) Reynolds number: 500,000 Max Cl/Cd: 90.23 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe675-il-500000-n5.txt Download as CSV file: xf-goe675-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5187 0.07928 0.07592 -0.0958 0.9270 0.0291
-14.000 -0.6046 0.06276 0.05911 -0.1075 0.9160 0.0291
-13.750 -0.6955 0.04472 0.04070 -0.1234 0.9021 0.0290
-13.500 -0.7266 0.03169 0.02718 -0.1403 0.8914 0.0290
-13.250 -0.7172 0.02945 0.02477 -0.1415 0.8866 0.0292
-13.000 -0.7029 0.02777 0.02296 -0.1421 0.8823 0.0294
-12.750 -0.6862 0.02636 0.02144 -0.1424 0.8778 0.0296
-12.500 -0.6679 0.02514 0.02010 -0.1425 0.8737 0.0298
-12.250 -0.6482 0.02405 0.01888 -0.1425 0.8700 0.0300
-12.000 -0.6273 0.02307 0.01777 -0.1425 0.8666 0.0303
-11.750 -0.6053 0.02215 0.01676 -0.1425 0.8630 0.0305
-11.500 -0.5827 0.02131 0.01582 -0.1424 0.8593 0.0308
-11.250 -0.5594 0.02053 0.01494 -0.1423 0.8556 0.0311
-11.000 -0.5356 0.01982 0.01411 -0.1422 0.8522 0.0313
-10.750 -0.5112 0.01916 0.01333 -0.1421 0.8491 0.0316
-10.500 -0.4862 0.01854 0.01262 -0.1420 0.8459 0.0319
-10.250 -0.4609 0.01796 0.01196 -0.1419 0.8424 0.0322
-10.000 -0.4355 0.01738 0.01130 -0.1418 0.8388 0.0325
-9.750 -0.4101 0.01678 0.01064 -0.1417 0.8355 0.0329
-9.500 -0.3842 0.01625 0.01004 -0.1417 0.8324 0.0334
-9.250 -0.3577 0.01579 0.00950 -0.1416 0.8294 0.0338
-9.000 -0.3310 0.01535 0.00902 -0.1416 0.8259 0.0344
-8.750 -0.3040 0.01495 0.00856 -0.1416 0.8225 0.0350
-8.500 -0.2768 0.01457 0.00812 -0.1415 0.8192 0.0357
-8.250 -0.2494 0.01422 0.00770 -0.1415 0.8158 0.0363
-8.000 -0.2220 0.01384 0.00726 -0.1415 0.8127 0.0370
-7.750 -0.1945 0.01349 0.00687 -0.1415 0.8094 0.0380
-7.500 -0.1668 0.01316 0.00652 -0.1415 0.8055 0.0390
-7.250 -0.1390 0.01287 0.00617 -0.1414 0.8009 0.0403
-7.000 -0.1112 0.01257 0.00582 -0.1414 0.7960 0.0419
-6.750 -0.0833 0.01230 0.00552 -0.1414 0.7915 0.0444
-6.500 -0.0553 0.01205 0.00529 -0.1414 0.7867 0.0477
-6.250 -0.0270 0.01186 0.00511 -0.1414 0.7821 0.0523
-6.000 0.0015 0.01173 0.00494 -0.1414 0.7775 0.0573
-5.750 0.0301 0.01162 0.00480 -0.1414 0.7727 0.0618
-5.500 0.0588 0.01153 0.00471 -0.1415 0.7678 0.0649
-5.250 0.0874 0.01145 0.00457 -0.1415 0.7626 0.0679
-5.000 0.1158 0.01134 0.00441 -0.1415 0.7576 0.0700
-4.750 0.1443 0.01124 0.00432 -0.1415 0.7518 0.0721
-4.500 0.1728 0.01115 0.00418 -0.1415 0.7457 0.0741
-4.250 0.2012 0.01108 0.00403 -0.1414 0.7399 0.0758
-4.000 0.2294 0.01094 0.00389 -0.1414 0.7332 0.0774
-3.750 0.2576 0.01084 0.00377 -0.1414 0.7265 0.0793
-3.500 0.2859 0.01078 0.00368 -0.1414 0.7207 0.0816
-3.250 0.3144 0.01070 0.00359 -0.1414 0.7145 0.0836
-3.000 0.3426 0.01064 0.00348 -0.1414 0.7081 0.0849
-2.750 0.3706 0.01051 0.00334 -0.1413 0.7017 0.0867
-2.500 0.3985 0.01043 0.00326 -0.1413 0.6937 0.0889
-2.250 0.4263 0.01039 0.00318 -0.1411 0.6860 0.0912
-2.000 0.4544 0.01033 0.00311 -0.1411 0.6780 0.0931
-1.750 0.4819 0.01031 0.00302 -0.1409 0.6698 0.0944
-1.500 0.5096 0.01024 0.00295 -0.1408 0.6605 0.0959
-1.250 0.5366 0.01022 0.00289 -0.1405 0.6505 0.0979
-1.000 0.5638 0.01019 0.00285 -0.1403 0.6393 0.1001
-0.750 0.5908 0.01021 0.00283 -0.1401 0.6287 0.1027
-0.500 0.6172 0.01025 0.00281 -0.1397 0.6166 0.1056
-0.250 0.6436 0.01027 0.00282 -0.1394 0.6028 0.1102
0.000 0.6693 0.01033 0.00284 -0.1389 0.5875 0.1156
0.250 0.6945 0.01042 0.00288 -0.1383 0.5707 0.1228
0.750 0.7433 0.01066 0.00303 -0.1369 0.5331 0.1438
1.000 0.7663 0.01084 0.00314 -0.1360 0.5113 0.1566
1.250 0.7888 0.01104 0.00327 -0.1350 0.4905 0.1729
1.500 0.8116 0.01120 0.00343 -0.1341 0.4732 0.2009
1.750 0.8354 0.01129 0.00360 -0.1334 0.4598 0.2481
2.000 0.8591 0.01142 0.00376 -0.1327 0.4490 0.2854
2.250 0.8824 0.01157 0.00394 -0.1319 0.4388 0.3168
2.500 0.9066 0.01166 0.00410 -0.1313 0.4305 0.3566
2.750 0.9303 0.01170 0.00430 -0.1307 0.4230 0.4301
3.000 0.9534 0.01158 0.00454 -0.1301 0.4171 0.5831
3.250 0.9761 0.01095 0.00480 -0.1287 0.4116 1.0000
3.500 0.9992 0.01118 0.00497 -0.1279 0.4056 1.0000
3.750 1.0209 0.01144 0.00517 -0.1268 0.4001 1.0000
4.000 1.0441 0.01161 0.00534 -0.1259 0.3959 1.0000
4.250 1.0665 0.01182 0.00552 -0.1249 0.3914 1.0000
4.500 1.0880 0.01206 0.00573 -0.1238 0.3865 1.0000
4.750 1.1086 0.01237 0.00599 -0.1225 0.3815 1.0000
5.000 1.1316 0.01258 0.00620 -0.1217 0.3768 1.0000
5.250 1.1537 0.01283 0.00644 -0.1208 0.3712 1.0000
5.500 1.1739 0.01317 0.00673 -0.1195 0.3649 1.0000
5.750 1.1957 0.01345 0.00700 -0.1186 0.3591 1.0000
6.000 1.2170 0.01375 0.00729 -0.1176 0.3523 1.0000
6.250 1.2364 0.01415 0.00764 -0.1163 0.3457 1.0000
6.500 1.2585 0.01444 0.00794 -0.1155 0.3407 1.0000
6.750 1.2797 0.01477 0.00826 -0.1146 0.3354 1.0000
7.000 1.2995 0.01517 0.00865 -0.1135 0.3300 1.0000
7.250 1.3199 0.01555 0.00903 -0.1125 0.3249 1.0000
7.500 1.3408 0.01592 0.00940 -0.1116 0.3193 1.0000
7.750 1.3597 0.01638 0.00985 -0.1104 0.3131 1.0000
8.000 1.3789 0.01684 0.01030 -0.1093 0.3060 1.0000
8.250 1.3967 0.01738 0.01081 -0.1081 0.2971 1.0000
8.500 1.4149 0.01792 0.01133 -0.1069 0.2896 1.0000
8.750 1.4323 0.01849 0.01190 -0.1057 0.2814 1.0000
9.000 1.4496 0.01909 0.01248 -0.1045 0.2742 1.0000
9.250 1.4656 0.01977 0.01314 -0.1031 0.2649 1.0000
9.500 1.4818 0.02045 0.01381 -0.1018 0.2560 1.0000
9.750 1.4953 0.02130 0.01462 -0.1002 0.2452 1.0000
10.000 1.5072 0.02227 0.01552 -0.0985 0.2310 1.0000
10.250 1.5178 0.02334 0.01652 -0.0967 0.2160 1.0000
10.500 1.5276 0.02449 0.01760 -0.0949 0.2008 1.0000
10.750 1.5358 0.02575 0.01880 -0.0930 0.1856 1.0000
11.000 1.5437 0.02707 0.02006 -0.0911 0.1714 1.0000
11.250 1.5507 0.02849 0.02142 -0.0892 0.1585 1.0000
11.500 1.5574 0.02995 0.02283 -0.0873 0.1460 1.0000
11.750 1.5614 0.03166 0.02448 -0.0853 0.1302 1.0000
12.000 1.5616 0.03373 0.02646 -0.0831 0.1114 1.0000
12.250 1.5594 0.03608 0.02870 -0.0809 0.0923 1.0000
12.500 1.5579 0.03845 0.03101 -0.0789 0.0785 1.0000
12.750 1.5573 0.04083 0.03336 -0.0772 0.0661 1.0000
13.000 1.5465 0.04426 0.03669 -0.0750 0.0452 1.0000
13.250 1.5457 0.04687 0.03931 -0.0736 0.0398 1.0000
13.500 1.5480 0.04925 0.04172 -0.0725 0.0375 1.0000
13.750 1.5501 0.05171 0.04424 -0.0716 0.0358 1.0000
14.000 1.5537 0.05407 0.04667 -0.0708 0.0347 1.0000
14.250 1.5563 0.05658 0.04925 -0.0700 0.0339 1.0000
14.500 1.5577 0.05927 0.05201 -0.0693 0.0332 1.0000
14.750 1.5584 0.06210 0.05492 -0.0688 0.0326 1.0000
15.000 1.5580 0.06512 0.05801 -0.0683 0.0321 1.0000
15.250 1.5560 0.06840 0.06137 -0.0679 0.0316 1.0000
15.500 1.5528 0.07185 0.06491 -0.0676 0.0312 1.0000
15.750 1.5513 0.07517 0.06832 -0.0674 0.0309 1.0000
16.000 1.5489 0.07866 0.07192 -0.0674 0.0306 1.0000
16.250 1.5455 0.08233 0.07568 -0.0675 0.0303 1.0000
16.500 1.5415 0.08613 0.07958 -0.0677 0.0300 1.0000
16.750 1.5366 0.09008 0.08362 -0.0679 0.0297 1.0000
17.000 1.5311 0.09415 0.08779 -0.0684 0.0294 1.0000
17.250 1.5250 0.09835 0.09208 -0.0689 0.0291 1.0000
17.500 1.5186 0.10264 0.09647 -0.0696 0.0288 1.0000
17.750 1.5118 0.10702 0.10094 -0.0703 0.0285 1.0000
18.000 1.5048 0.11143 0.10544 -0.0712 0.0283 1.0000
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Polar data table (+)
Polar graphs
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