GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Reynolds number: 100,000 Max Cl/Cd: 64.03 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe198-il-100000-n5.txt Download as CSV file: xf-goe198-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 198 (L.F.G. 5294) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2709 0.12208 0.11707 -0.0343 1.0000 0.0401
-9.500 -0.2744 0.12037 0.11542 -0.0322 1.0000 0.0405
-9.250 -0.2796 0.11899 0.11409 -0.0300 1.0000 0.0410
-9.000 -0.2739 0.11647 0.11159 -0.0307 0.9977 0.0417
-8.750 -0.2604 0.11324 0.10835 -0.0338 0.9939 0.0428
-8.500 -0.2482 0.11025 0.10536 -0.0368 0.9892 0.0443
-8.250 -0.2355 0.10785 0.10295 -0.0420 0.9838 0.0458
-8.000 -0.2280 0.10622 0.10132 -0.0473 0.9754 0.0462
-7.750 -0.2109 0.10249 0.09760 -0.0519 0.9705 0.0465
-7.500 -0.1952 0.09797 0.09307 -0.0516 0.9670 0.0471
-7.250 -0.1755 0.09424 0.08932 -0.0547 0.9626 0.0481
-7.000 -0.1528 0.09064 0.08570 -0.0595 0.9588 0.0494
-6.750 -0.1371 0.08777 0.08281 -0.0629 0.9513 0.0508
-6.500 -0.1080 0.08481 0.07979 -0.0723 0.9456 0.0532
-6.250 -0.0814 0.08216 0.07708 -0.0816 0.9370 0.0539
-6.000 -0.0659 0.07798 0.07291 -0.0805 0.9330 0.0546
-5.750 -0.0412 0.07445 0.06934 -0.0837 0.9293 0.0558
-5.250 0.0042 0.06885 0.06367 -0.0911 0.9165 0.0591
-5.000 0.0522 0.06622 0.06082 -0.1036 0.9115 0.0616
-4.750 0.0761 0.06316 0.05771 -0.1069 0.9048 0.0621
-4.500 0.0913 0.05997 0.05457 -0.1060 0.9006 0.0633
-4.250 0.1185 0.05726 0.05180 -0.1087 0.8971 0.0658
-4.000 0.1461 0.05507 0.04952 -0.1123 0.8895 0.0687
-3.750 0.2059 0.05282 0.04686 -0.1235 0.8850 0.0710
-3.500 0.2249 0.04942 0.04353 -0.1237 0.8804 0.0717
-3.250 0.2451 0.04712 0.04123 -0.1241 0.8730 0.0729
-3.000 0.2759 0.04477 0.03880 -0.1265 0.8685 0.0748
-2.750 0.3074 0.04274 0.03665 -0.1290 0.8620 0.0773
-2.500 0.3569 0.04112 0.03457 -0.1347 0.8555 0.0819
-2.250 0.3795 0.03828 0.03183 -0.1351 0.8502 0.0841
-2.000 0.4056 0.03664 0.03012 -0.1358 0.8407 0.0873
-1.750 0.4587 0.03309 0.02586 -0.1401 0.8356 0.0616
-1.250 0.5224 0.02879 0.02112 -0.1422 0.8197 0.0532
-1.000 0.5503 0.02744 0.01965 -0.1426 0.8095 0.0524
-0.750 0.5829 0.02593 0.01788 -0.1433 0.8025 0.0517
-0.500 0.6132 0.02471 0.01636 -0.1435 0.7921 0.0529
-0.250 0.6442 0.02355 0.01484 -0.1437 0.7828 0.0537
0.000 0.6741 0.02249 0.01356 -0.1437 0.7734 0.0536
0.250 0.7022 0.02163 0.01253 -0.1435 0.7616 0.0538
0.500 0.7305 0.02083 0.01161 -0.1432 0.7499 0.0544
0.750 0.7593 0.02012 0.01078 -0.1429 0.7386 0.0553
1.000 0.7867 0.01960 0.01020 -0.1426 0.7259 0.0567
1.250 0.8138 0.01921 0.00973 -0.1421 0.7134 0.0602
1.500 0.8414 0.01880 0.00927 -0.1417 0.7007 0.0635
1.750 0.8689 0.01841 0.00884 -0.1413 0.6876 0.0665
2.000 0.8959 0.01809 0.00840 -0.1407 0.6738 0.0706
2.250 0.9229 0.01782 0.00809 -0.1402 0.6593 0.0773
2.500 0.9499 0.01766 0.00786 -0.1398 0.6445 0.0929
2.750 0.9772 0.01750 0.00770 -0.1394 0.6297 0.1210
3.000 0.9973 0.01604 0.00773 -0.1378 0.6142 1.0000
3.250 1.0234 0.01625 0.00767 -0.1371 0.5964 1.0000
3.500 1.0488 0.01650 0.00770 -0.1364 0.5767 1.0000
3.750 1.0735 0.01681 0.00781 -0.1356 0.5556 1.0000
4.000 1.0980 0.01717 0.00797 -0.1348 0.5352 1.0000
4.250 1.1224 0.01753 0.00822 -0.1341 0.5172 1.0000
4.500 1.1468 0.01791 0.00849 -0.1334 0.5006 1.0000
4.750 1.1709 0.01829 0.00881 -0.1328 0.4841 1.0000
5.000 1.1944 0.01868 0.00914 -0.1320 0.4661 1.0000
5.250 1.2174 0.01909 0.00950 -0.1312 0.4470 1.0000
5.500 1.2401 0.01951 0.00987 -0.1303 0.4281 1.0000
5.750 1.2626 0.01995 0.01026 -0.1294 0.4107 1.0000
6.000 1.2844 0.02042 0.01069 -0.1285 0.3939 1.0000
6.250 1.3053 0.02096 0.01114 -0.1274 0.3771 1.0000
6.500 1.3257 0.02153 0.01163 -0.1262 0.3625 1.0000
6.750 1.3458 0.02214 0.01217 -0.1250 0.3500 1.0000
7.000 1.3664 0.02271 0.01277 -0.1239 0.3386 1.0000
7.250 1.3867 0.02331 0.01338 -0.1228 0.3288 1.0000
7.500 1.4063 0.02393 0.01402 -0.1216 0.3195 1.0000
7.750 1.4262 0.02452 0.01471 -0.1205 0.3103 1.0000
8.000 1.4436 0.02521 0.01541 -0.1189 0.2993 1.0000
8.250 1.4620 0.02582 0.01613 -0.1176 0.2885 1.0000
8.500 1.4795 0.02646 0.01688 -0.1161 0.2785 1.0000
8.750 1.4947 0.02717 0.01766 -0.1142 0.2668 1.0000
9.000 1.5087 0.02789 0.01850 -0.1123 0.2507 1.0000
9.250 1.5198 0.02867 0.01937 -0.1098 0.2296 1.0000
9.500 1.5283 0.02967 0.02037 -0.1072 0.2048 1.0000
9.750 1.5313 0.03111 0.02166 -0.1041 0.1745 1.0000
10.000 1.5325 0.03288 0.02328 -0.1011 0.1478 1.0000
10.250 1.5340 0.03478 0.02511 -0.0984 0.1241 1.0000
10.500 1.5352 0.03680 0.02706 -0.0958 0.1079 1.0000
10.750 1.5367 0.03884 0.02911 -0.0935 0.0976 1.0000
11.000 1.5380 0.04096 0.03126 -0.0913 0.0906 1.0000
11.250 1.5369 0.04335 0.03368 -0.0891 0.0850 1.0000
11.500 1.5365 0.04574 0.03617 -0.0872 0.0807 1.0000
11.750 1.5342 0.04840 0.03892 -0.0854 0.0771 1.0000
12.000 1.5288 0.05146 0.04209 -0.0838 0.0744 1.0000
12.250 1.5250 0.05448 0.04524 -0.0824 0.0719 1.0000
12.500 1.5209 0.05764 0.04857 -0.0813 0.0695 1.0000
12.750 1.5144 0.06120 0.05226 -0.0804 0.0673 1.0000
13.000 1.5049 0.06522 0.05638 -0.0797 0.0652 1.0000
13.250 1.4961 0.06929 0.06053 -0.0792 0.0632 1.0000
13.500 1.4931 0.07284 0.06428 -0.0789 0.0610 1.0000
13.750 1.4886 0.07664 0.06823 -0.0788 0.0588 1.0000
14.000 1.4833 0.08056 0.07225 -0.0788 0.0567 1.0000
14.250 1.4785 0.08417 0.07589 -0.0784 0.0546 1.0000
14.500 1.4768 0.08780 0.07973 -0.0785 0.0521 1.0000
14.750 1.4742 0.09159 0.08369 -0.0788 0.0493 1.0000
15.000 1.4715 0.09522 0.08738 -0.0790 0.0467 1.0000
15.250 1.4690 0.09902 0.09133 -0.0794 0.0440 1.0000
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Polar data table (+)
Polar graphs
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