GOE 692 AIRFOIL (goe692-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 692 AIRFOIL (goe692-il) Reynolds number: 200,000 Max Cl/Cd: 76.13 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe692-il-200000.txt Download as CSV file: xf-goe692-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 692 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1806 0.10254 0.09876 -0.0823 0.9714 0.0900
-9.750 -0.3159 0.06424 0.06035 -0.1165 0.9571 0.0690
-9.500 -0.3250 0.05920 0.05524 -0.1196 0.9474 0.0684
-9.250 -0.3597 0.04789 0.04346 -0.1265 0.9385 0.0667
-9.000 -0.3869 0.03975 0.03460 -0.1266 0.9279 0.0662
-8.750 -0.3836 0.03541 0.02968 -0.1261 0.9213 0.0668
-8.500 -0.3721 0.03248 0.02625 -0.1253 0.9144 0.0678
-8.250 -0.3476 0.02991 0.02314 -0.1262 0.9111 0.0695
-8.000 -0.3134 0.02849 0.02173 -0.1281 0.9091 0.0713
-7.750 -0.2990 0.02784 0.02101 -0.1260 0.9000 0.0727
-7.500 -0.2700 0.02649 0.01944 -0.1266 0.8962 0.0749
-7.250 -0.2387 0.02513 0.01766 -0.1275 0.8933 0.0774
-7.000 -0.2182 0.02405 0.01660 -0.1265 0.8861 0.0796
-6.750 -0.1902 0.02341 0.01593 -0.1267 0.8807 0.0828
-6.500 -0.1585 0.02261 0.01485 -0.1273 0.8771 0.0869
-6.250 -0.1305 0.02167 0.01398 -0.1276 0.8726 0.0907
-6.000 -0.1080 0.02127 0.01351 -0.1266 0.8649 0.0948
-5.750 -0.0777 0.02046 0.01261 -0.1270 0.8605 0.1000
-5.500 -0.0447 0.02002 0.01214 -0.1279 0.8572 0.1059
-5.250 -0.0251 0.01969 0.01173 -0.1264 0.8482 0.1109
-5.000 0.0045 0.01933 0.01140 -0.1266 0.8433 0.1167
-4.750 0.0369 0.01885 0.01078 -0.1273 0.8397 0.1234
-4.500 0.0578 0.01874 0.01075 -0.1261 0.8310 0.1288
-4.250 0.0873 0.01853 0.01039 -0.1262 0.8258 0.1358
-4.000 0.1188 0.01805 0.00996 -0.1268 0.8220 0.1431
-3.750 0.1409 0.01805 0.00990 -0.1257 0.8136 0.1503
-3.500 0.1691 0.01761 0.00953 -0.1257 0.8082 0.1582
-3.250 0.2010 0.01733 0.00912 -0.1262 0.8042 0.1679
-3.000 0.2229 0.01714 0.00905 -0.1252 0.7962 0.1771
-2.750 0.2509 0.01681 0.00872 -0.1251 0.7906 0.1891
-2.500 0.2823 0.01654 0.00838 -0.1256 0.7865 0.2033
-2.250 0.3048 0.01643 0.00836 -0.1247 0.7790 0.2162
-2.000 0.3322 0.01617 0.00814 -0.1245 0.7733 0.2305
-1.750 0.3630 0.01589 0.00785 -0.1250 0.7692 0.2460
-1.500 0.3868 0.01583 0.00785 -0.1243 0.7624 0.2608
-1.250 0.4135 0.01566 0.00772 -0.1240 0.7566 0.2784
-1.000 0.4434 0.01535 0.00749 -0.1243 0.7523 0.3007
-0.750 0.4681 0.01520 0.00749 -0.1238 0.7463 0.3298
-0.500 0.4924 0.01489 0.00746 -0.1233 0.7401 0.3846
-0.250 0.5154 0.01406 0.00739 -0.1223 0.7356 0.5832
0.000 0.5339 0.01349 0.00767 -0.1189 0.7308 0.8582
0.250 0.5873 0.01359 0.00782 -0.1233 0.7246 0.9650
0.500 0.6560 0.01356 0.00765 -0.1316 0.7198 0.9940
0.750 0.6990 0.01353 0.00746 -0.1347 0.7154 1.0000
1.000 0.7152 0.01370 0.00762 -0.1327 0.7081 1.0000
1.250 0.7395 0.01372 0.00754 -0.1320 0.7025 1.0000
1.500 0.7661 0.01375 0.00745 -0.1317 0.6977 1.0000
1.750 0.7837 0.01394 0.00764 -0.1298 0.6904 1.0000
2.000 0.8096 0.01397 0.00757 -0.1294 0.6848 1.0000
2.250 0.8346 0.01407 0.00759 -0.1288 0.6792 1.0000
2.500 0.8545 0.01423 0.00775 -0.1273 0.6720 1.0000
2.750 0.8824 0.01426 0.00767 -0.1272 0.6663 1.0000
3.000 0.9036 0.01443 0.00782 -0.1259 0.6589 1.0000
3.250 0.9286 0.01447 0.00779 -0.1253 0.6510 1.0000
3.500 0.9530 0.01456 0.00782 -0.1245 0.6431 1.0000
3.750 0.9762 0.01466 0.00789 -0.1235 0.6347 1.0000
4.000 1.0048 0.01478 0.00790 -0.1236 0.6285 1.0000
4.250 1.0242 0.01498 0.00814 -0.1220 0.6200 1.0000
4.500 1.0528 0.01507 0.00813 -0.1221 0.6131 1.0000
4.750 1.0724 0.01527 0.00837 -0.1205 0.6041 1.0000
5.000 1.0992 0.01535 0.00837 -0.1203 0.5962 1.0000
5.250 1.1192 0.01555 0.00859 -0.1188 0.5870 1.0000
5.500 1.1448 0.01563 0.00861 -0.1183 0.5786 1.0000
5.750 1.1640 0.01583 0.00885 -0.1167 0.5690 1.0000
6.000 1.1895 0.01593 0.00887 -0.1162 0.5604 1.0000
6.250 1.2062 0.01612 0.00912 -0.1141 0.5498 1.0000
6.500 1.2295 0.01626 0.00920 -0.1132 0.5406 1.0000
6.750 1.2466 0.01647 0.00946 -0.1113 0.5303 1.0000
7.000 1.2669 0.01668 0.00965 -0.1099 0.5207 1.0000
7.250 1.2858 0.01689 0.00985 -0.1083 0.5106 1.0000
7.500 1.3021 0.01716 0.01016 -0.1062 0.5001 1.0000
7.750 1.3212 0.01742 0.01036 -0.1047 0.4901 1.0000
8.000 1.3341 0.01773 0.01070 -0.1020 0.4786 1.0000
8.250 1.3467 0.01808 0.01105 -0.0993 0.4675 1.0000
8.500 1.3611 0.01847 0.01138 -0.0970 0.4564 1.0000
8.750 1.3719 0.01893 0.01186 -0.0942 0.4440 1.0000
9.000 1.3830 0.01946 0.01239 -0.0915 0.4315 1.0000
9.250 1.3941 0.02005 0.01295 -0.0890 0.4189 1.0000
9.500 1.4046 0.02070 0.01355 -0.0864 0.4060 1.0000
9.750 1.4130 0.02145 0.01429 -0.0836 0.3922 1.0000
10.000 1.4205 0.02229 0.01513 -0.0809 0.3779 1.0000
10.250 1.4275 0.02322 0.01605 -0.0783 0.3635 1.0000
10.500 1.4336 0.02425 0.01706 -0.0756 0.3491 1.0000
10.750 1.4390 0.02540 0.01817 -0.0730 0.3347 1.0000
11.000 1.4437 0.02665 0.01937 -0.0705 0.3209 1.0000
11.250 1.4478 0.02800 0.02065 -0.0681 0.3076 1.0000
11.500 1.4526 0.02940 0.02204 -0.0658 0.2944 1.0000
11.750 1.4573 0.03085 0.02350 -0.0637 0.2821 1.0000
12.000 1.4617 0.03238 0.02497 -0.0616 0.2711 1.0000
12.250 1.4660 0.03396 0.02649 -0.0597 0.2606 1.0000
12.500 1.4718 0.03550 0.02806 -0.0579 0.2506 1.0000
12.750 1.4784 0.03699 0.02944 -0.0562 0.2422 1.0000
13.000 1.4851 0.03855 0.03109 -0.0547 0.2340 1.0000
13.250 1.4945 0.03990 0.03231 -0.0533 0.2269 1.0000
13.500 1.5007 0.04155 0.03409 -0.0520 0.2201 1.0000
13.750 1.5092 0.04300 0.03549 -0.0507 0.2140 1.0000
14.000 1.5178 0.04449 0.03703 -0.0496 0.2083 1.0000
14.250 1.5231 0.04627 0.03889 -0.0484 0.2025 1.0000
14.500 1.5329 0.04763 0.04013 -0.0474 0.1965 1.0000
14.750 1.5347 0.04982 0.04250 -0.0464 0.1914 1.0000
15.000 1.5397 0.05172 0.04447 -0.0455 0.1866 1.0000
15.250 1.5497 0.05309 0.04576 -0.0446 0.1819 1.0000
15.500 1.5535 0.05522 0.04806 -0.0438 0.1780 1.0000
15.750 1.5572 0.05738 0.05032 -0.0431 0.1736 1.0000
16.000 1.5619 0.05940 0.05235 -0.0425 0.1694 1.0000
16.250 1.5680 0.06130 0.05428 -0.0418 0.1653 1.0000
16.500 1.5696 0.06381 0.05697 -0.0414 0.1615 1.0000
16.750 1.5726 0.06616 0.05940 -0.0410 0.1579 1.0000
17.000 1.5788 0.06806 0.06127 -0.0405 0.1541 1.0000
17.250 1.5813 0.07052 0.06386 -0.0401 0.1508 1.0000
17.500 1.5812 0.07338 0.06688 -0.0400 0.1472 1.0000
17.750 1.5816 0.07616 0.06973 -0.0399 0.1435 1.0000
18.000 1.5877 0.07803 0.07152 -0.0395 0.1395 1.0000
18.250 1.5825 0.08172 0.07545 -0.0398 0.1362 1.0000
18.500 1.5792 0.08515 0.07903 -0.0402 0.1322 1.0000
18.750 1.5778 0.08823 0.08212 -0.0404 0.1282 1.0000
19.000 1.5743 0.09173 0.08574 -0.0408 0.1243 1.0000
19.250 1.5675 0.09585 0.09003 -0.0417 0.1200 1.0000
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Polar data table (+)
Polar graphs
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