GOE 395 AIRFOIL (goe395-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 395 AIRFOIL (goe395-il) Reynolds number: 100,000 Max Cl/Cd: 71.02 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe395-il-100000-n5.txt Download as CSV file: xf-goe395-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 395 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1727 0.10076 0.09591 -0.0559 0.9177 0.0465
-8.000 -0.1658 0.09962 0.09477 -0.0601 0.9059 0.0472
-7.750 -0.1568 0.09832 0.09345 -0.0655 0.8962 0.0475
-7.500 -0.1453 0.09253 0.08766 -0.0625 0.8930 0.0485
-7.250 -0.1328 0.08921 0.08430 -0.0625 0.8887 0.0499
-7.000 -0.1201 0.08651 0.08159 -0.0642 0.8829 0.0514
-6.750 -0.1062 0.08384 0.07890 -0.0667 0.8779 0.0532
-6.500 -0.0868 0.08175 0.07675 -0.0731 0.8731 0.0573
-6.250 -0.0522 0.08012 0.07502 -0.0878 0.8666 0.0585
-6.000 -0.0451 0.07552 0.07045 -0.0847 0.8636 0.0593
-5.750 -0.0319 0.07220 0.06710 -0.0839 0.8607 0.0604
-5.500 -0.0133 0.06937 0.06424 -0.0859 0.8572 0.0619
-5.250 0.0087 0.06681 0.06165 -0.0893 0.8537 0.0655
-5.000 0.0700 0.06431 0.05889 -0.1084 0.8500 0.0706
-4.500 0.1272 0.05711 0.05147 -0.1171 0.8455 0.0705
-4.000 0.1857 0.04803 0.04216 -0.1260 0.8396 0.0582
-3.750 0.2097 0.04556 0.03964 -0.1276 0.8368 0.0573
-3.500 0.2432 0.04257 0.03650 -0.1318 0.8346 0.0566
-3.250 0.2875 0.03869 0.03233 -0.1390 0.8328 0.0574
-3.000 0.3348 0.03424 0.02746 -0.1463 0.8313 0.0584
-2.750 0.3703 0.03133 0.02426 -0.1498 0.8292 0.0583
-2.500 0.4072 0.02818 0.02069 -0.1536 0.8264 0.0585
-2.250 0.4379 0.02661 0.01890 -0.1553 0.8237 0.0595
-2.000 0.4685 0.02537 0.01743 -0.1565 0.8207 0.0609
-1.750 0.4993 0.02425 0.01606 -0.1572 0.8172 0.0633
-1.500 0.5301 0.02307 0.01446 -0.1580 0.8125 0.0688
-1.250 0.5594 0.02195 0.01301 -0.1584 0.8067 0.0720
-1.000 0.5880 0.02136 0.01230 -0.1583 0.8026 0.0754
-0.750 0.6171 0.02068 0.01137 -0.1584 0.7988 0.0815
-0.500 0.6440 0.02030 0.01089 -0.1583 0.7938 0.0883
-0.250 0.6716 0.02012 0.01056 -0.1581 0.7896 0.0999
0.000 0.6994 0.01998 0.01040 -0.1579 0.7860 0.1118
0.250 0.7252 0.01996 0.01042 -0.1576 0.7807 0.1226
0.500 0.7518 0.01982 0.01026 -0.1573 0.7755 0.1320
0.750 0.7796 0.01957 0.00997 -0.1569 0.7713 0.1388
1.000 0.8057 0.01949 0.00987 -0.1565 0.7656 0.1438
1.250 0.8322 0.01939 0.00982 -0.1560 0.7598 0.1505
1.500 0.8602 0.01920 0.00958 -0.1556 0.7554 0.1592
1.750 0.8852 0.01925 0.00972 -0.1550 0.7484 0.1664
2.000 0.9121 0.01914 0.00963 -0.1545 0.7428 0.1753
2.250 0.9387 0.01907 0.00961 -0.1539 0.7371 0.1883
2.500 0.9641 0.01905 0.00975 -0.1534 0.7296 0.2102
2.750 0.9919 0.01869 0.00969 -0.1529 0.7246 0.2972
3.000 1.0125 0.01793 0.00999 -0.1516 0.7156 1.0000
3.250 1.0403 0.01790 0.00988 -0.1510 0.7096 1.0000
3.500 1.0641 0.01813 0.01015 -0.1502 0.6997 1.0000
3.750 1.0907 0.01813 0.01013 -0.1495 0.6922 1.0000
4.000 1.1152 0.01825 0.01033 -0.1487 0.6816 1.0000
4.250 1.1393 0.01835 0.01049 -0.1478 0.6693 1.0000
4.500 1.1632 0.01838 0.01059 -0.1468 0.6551 1.0000
4.750 1.1868 0.01842 0.01070 -0.1458 0.6384 1.0000
5.000 1.2102 0.01846 0.01085 -0.1447 0.6187 1.0000
5.250 1.2334 0.01851 0.01096 -0.1436 0.5958 1.0000
5.500 1.2584 0.01837 0.01079 -0.1424 0.5717 1.0000
5.750 1.2835 0.01825 0.01056 -0.1411 0.5455 1.0000
6.000 1.3067 0.01840 0.01052 -0.1397 0.5180 1.0000
6.250 1.3283 0.01884 0.01083 -0.1383 0.4917 1.0000
6.500 1.3494 0.01938 0.01131 -0.1370 0.4680 1.0000
6.750 1.3693 0.01999 0.01186 -0.1355 0.4429 1.0000
7.000 1.3880 0.02065 0.01253 -0.1340 0.4157 1.0000
7.250 1.4063 0.02134 0.01321 -0.1325 0.3897 1.0000
7.500 1.4235 0.02208 0.01394 -0.1308 0.3634 1.0000
7.750 1.4387 0.02293 0.01475 -0.1289 0.3321 1.0000
8.000 1.4498 0.02402 0.01568 -0.1265 0.2896 1.0000
8.250 1.4566 0.02540 0.01682 -0.1237 0.2350 1.0000
8.500 1.4598 0.02708 0.01815 -0.1206 0.1858 1.0000
8.750 1.4629 0.02869 0.01956 -0.1175 0.1568 1.0000
9.000 1.4666 0.03036 0.02110 -0.1147 0.1347 1.0000
9.250 1.4713 0.03201 0.02269 -0.1122 0.1155 1.0000
9.500 1.4781 0.03355 0.02426 -0.1100 0.0987 1.0000
9.750 1.4845 0.03518 0.02590 -0.1079 0.0788 1.0000
10.000 1.4871 0.03719 0.02781 -0.1057 0.0604 1.0000
10.250 1.4877 0.03945 0.03004 -0.1034 0.0470 1.0000
10.500 1.4877 0.04185 0.03252 -0.1012 0.0388 1.0000
10.750 1.4881 0.04427 0.03501 -0.0991 0.0337 1.0000
11.000 1.4887 0.04672 0.03756 -0.0973 0.0304 1.0000
11.250 1.4896 0.04919 0.04014 -0.0955 0.0276 1.0000
11.750 1.4869 0.05474 0.04593 -0.0923 0.0244 1.0000
12.000 1.4853 0.05762 0.04899 -0.0908 0.0234 1.0000
12.250 1.4832 0.06063 0.05216 -0.0895 0.0226 1.0000
12.500 1.4807 0.06372 0.05542 -0.0882 0.0218 1.0000
12.750 1.4779 0.06691 0.05876 -0.0871 0.0211 1.0000
13.000 1.4746 0.07023 0.06221 -0.0861 0.0204 1.0000
13.250 1.4703 0.07377 0.06587 -0.0853 0.0198 1.0000
13.500 1.4648 0.07752 0.06977 -0.0845 0.0191 1.0000
13.750 1.4633 0.08094 0.07338 -0.0838 0.0185 1.0000
14.000 1.4614 0.08451 0.07718 -0.0834 0.0180 1.0000
14.250 1.4587 0.08829 0.08118 -0.0831 0.0175 1.0000
14.500 1.4552 0.09227 0.08538 -0.0830 0.0172 1.0000
14.750 1.4508 0.09653 0.08986 -0.0832 0.0169 1.0000
15.000 1.4449 0.10117 0.09474 -0.0838 0.0167 1.0000
15.250 1.4378 0.10618 0.09999 -0.0849 0.0165 1.0000
15.500 1.4291 0.11162 0.10568 -0.0865 0.0164 1.0000
15.750 1.4191 0.11754 0.11184 -0.0887 0.0163 1.0000
16.000 1.4078 0.12398 0.11851 -0.0916 0.0162 1.0000
16.250 1.3952 0.13101 0.12579 -0.0952 0.0162 1.0000
16.500 1.3811 0.13875 0.13376 -0.0996 0.0162 1.0000
16.750 1.3653 0.14738 0.14262 -0.1049 0.0163 1.0000
17.000 1.3477 0.15709 0.15255 -0.1114 0.0164 1.0000
17.250 1.3278 0.16842 0.16408 -0.1192 0.0166 1.0000
17.500 1.3043 0.18245 0.17828 -0.1289 0.0170 1.0000
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