GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 501 AIRFOIL (goe501-il) Reynolds number: 100,000 Max Cl/Cd: 60.47 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe501-il-100000-n5.txt Download as CSV file: xf-goe501-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 501 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1500 0.09403 0.08869 -0.0861 0.9487 0.0593
-9.000 -0.1431 0.08869 0.08332 -0.0919 0.9446 0.0601
-8.750 -0.1533 0.08340 0.07805 -0.0957 0.9345 0.0608
-8.500 -0.1295 0.08226 0.07690 -0.0963 0.9316 0.0621
-8.250 -0.1271 0.07833 0.07296 -0.0991 0.9248 0.0621
-8.000 -0.1273 0.07481 0.06945 -0.1011 0.9165 0.0624
-7.750 -0.1106 0.07177 0.06639 -0.1047 0.9128 0.0638
-7.500 -0.1186 0.06884 0.06348 -0.1050 0.9014 0.0644
-7.000 -0.1304 0.03979 0.03341 -0.1432 0.8819 0.0663
-6.750 -0.1200 0.03610 0.02916 -0.1456 0.8733 0.0681
-6.500 -0.0888 0.03272 0.02496 -0.1500 0.8697 0.0704
-6.250 -0.0554 0.03094 0.02308 -0.1522 0.8673 0.0720
-6.000 -0.0293 0.02966 0.02162 -0.1527 0.8619 0.0735
-5.750 -0.0029 0.02849 0.02025 -0.1531 0.8556 0.0755
-5.500 0.0332 0.02710 0.01855 -0.1551 0.8521 0.0786
-5.250 0.0717 0.02575 0.01681 -0.1573 0.8496 0.0812
-5.000 0.0890 0.02505 0.01612 -0.1557 0.8410 0.0828
-4.750 0.1208 0.02425 0.01529 -0.1566 0.8373 0.0856
-4.500 0.1556 0.02346 0.01438 -0.1580 0.8347 0.0894
-4.250 0.1800 0.02298 0.01375 -0.1574 0.8289 0.0924
-4.000 0.2064 0.02245 0.01324 -0.1573 0.8236 0.0953
-3.750 0.2396 0.02189 0.01266 -0.1582 0.8201 0.1000
-3.500 0.2757 0.02127 0.01196 -0.1596 0.8174 0.1059
-3.250 0.2952 0.02116 0.01189 -0.1582 0.8097 0.1106
-3.000 0.3265 0.02075 0.01143 -0.1587 0.8051 0.1183
-2.750 0.3619 0.02027 0.01093 -0.1599 0.8017 0.1307
-2.500 0.3863 0.02009 0.01077 -0.1593 0.7950 0.1451
-2.250 0.4153 0.01978 0.01047 -0.1594 0.7892 0.1657
-2.000 0.4501 0.01933 0.01008 -0.1605 0.7852 0.1931
-1.750 0.4756 0.01924 0.01002 -0.1600 0.7783 0.2163
-1.500 0.5040 0.01908 0.00991 -0.1599 0.7718 0.2389
-1.250 0.5393 0.01880 0.00962 -0.1610 0.7674 0.2668
-1.000 0.5614 0.01887 0.00974 -0.1598 0.7589 0.2882
-0.750 0.5926 0.01872 0.00959 -0.1601 0.7527 0.3130
-0.500 0.6224 0.01862 0.00947 -0.1602 0.7461 0.3375
-0.250 0.6473 0.01860 0.00950 -0.1595 0.7375 0.3601
0.000 0.6822 0.01835 0.00922 -0.1604 0.7320 0.3857
0.250 0.7024 0.01845 0.00937 -0.1589 0.7215 0.4049
0.500 0.7361 0.01822 0.00912 -0.1596 0.7151 0.4268
0.750 0.7574 0.01830 0.00926 -0.1583 0.7042 0.4455
1.000 0.7897 0.01810 0.00906 -0.1587 0.6968 0.4685
1.250 0.8113 0.01818 0.00921 -0.1574 0.6850 0.4906
1.500 0.8366 0.01815 0.00924 -0.1567 0.6743 0.5181
1.750 0.8650 0.01801 0.00915 -0.1564 0.6640 0.5550
2.000 0.8864 0.01803 0.00928 -0.1551 0.6508 0.6019
2.250 0.9087 0.01789 0.00936 -0.1537 0.6386 0.6710
2.500 0.9305 0.01736 0.00921 -0.1520 0.6277 1.0000
2.750 0.9570 0.01749 0.00921 -0.1516 0.6162 1.0000
3.000 0.9814 0.01768 0.00931 -0.1509 0.6041 1.0000
3.250 1.0072 0.01785 0.00936 -0.1503 0.5924 1.0000
3.500 1.0341 0.01799 0.00936 -0.1500 0.5814 1.0000
3.750 1.0590 0.01823 0.00951 -0.1494 0.5704 1.0000
4.000 1.0845 0.01848 0.00967 -0.1489 0.5609 1.0000
4.250 1.1108 0.01874 0.00983 -0.1485 0.5521 1.0000
4.500 1.1352 0.01907 0.01012 -0.1479 0.5436 1.0000
4.750 1.1612 0.01938 0.01036 -0.1475 0.5360 1.0000
5.000 1.1861 0.01973 0.01068 -0.1470 0.5288 1.0000
5.250 1.2103 0.02010 0.01104 -0.1464 0.5212 1.0000
5.500 1.2360 0.02046 0.01134 -0.1460 0.5140 1.0000
5.750 1.2578 0.02087 0.01179 -0.1450 0.5060 1.0000
6.000 1.2843 0.02124 0.01211 -0.1448 0.4997 1.0000
6.250 1.3055 0.02169 0.01263 -0.1438 0.4929 1.0000
6.500 1.3279 0.02211 0.01309 -0.1429 0.4859 1.0000
6.750 1.3509 0.02253 0.01352 -0.1421 0.4786 1.0000
7.000 1.3690 0.02300 0.01407 -0.1405 0.4703 1.0000
7.250 1.3922 0.02341 0.01446 -0.1398 0.4632 1.0000
7.500 1.4063 0.02392 0.01509 -0.1376 0.4543 1.0000
7.750 1.4270 0.02433 0.01550 -0.1364 0.4465 1.0000
8.000 1.4384 0.02489 0.01620 -0.1338 0.4379 1.0000
8.250 1.4555 0.02535 0.01666 -0.1320 0.4293 1.0000
8.500 1.4642 0.02598 0.01742 -0.1291 0.4188 1.0000
8.750 1.4749 0.02660 0.01810 -0.1265 0.4079 1.0000
9.000 1.4849 0.02724 0.01875 -0.1239 0.3963 1.0000
9.250 1.4912 0.02806 0.01969 -0.1210 0.3835 1.0000
9.500 1.4983 0.02893 0.02064 -0.1182 0.3707 1.0000
9.750 1.5050 0.02988 0.02165 -0.1156 0.3573 1.0000
10.000 1.5103 0.03096 0.02279 -0.1129 0.3424 1.0000
10.250 1.5140 0.03220 0.02407 -0.1102 0.3254 1.0000
10.500 1.5160 0.03364 0.02551 -0.1075 0.3060 1.0000
10.750 1.5164 0.03528 0.02711 -0.1048 0.2856 1.0000
11.000 1.5158 0.03713 0.02892 -0.1023 0.2656 1.0000
11.250 1.5145 0.03918 0.03092 -0.1000 0.2473 1.0000
11.500 1.5121 0.04143 0.03314 -0.0978 0.2318 1.0000
11.750 1.5103 0.04378 0.03546 -0.0959 0.2197 1.0000
12.000 1.5084 0.04624 0.03790 -0.0941 0.2100 1.0000
12.250 1.5086 0.04863 0.04033 -0.0926 0.2013 1.0000
12.500 1.5074 0.05122 0.04292 -0.0912 0.1939 1.0000
12.750 1.5080 0.05374 0.04551 -0.0900 0.1864 1.0000
13.000 1.5068 0.05648 0.04822 -0.0888 0.1799 1.0000
13.250 1.5092 0.05899 0.05089 -0.0880 0.1729 1.0000
13.500 1.5091 0.06176 0.05367 -0.0871 0.1663 1.0000
13.750 1.5113 0.06440 0.05643 -0.0864 0.1597 1.0000
14.000 1.5115 0.06733 0.05947 -0.0858 0.1526 1.0000
14.250 1.5118 0.07029 0.06249 -0.0854 0.1458 1.0000
14.500 1.5111 0.07359 0.06597 -0.0852 0.1377 1.0000
14.750 1.5094 0.07702 0.06951 -0.0852 0.1303 1.0000
15.000 1.5068 0.08073 0.07336 -0.0854 0.1222 1.0000
15.250 1.5045 0.08448 0.07723 -0.0858 0.1142 1.0000
15.500 1.4996 0.08869 0.08148 -0.0865 0.1073 1.0000
15.750 1.4959 0.09279 0.08567 -0.0872 0.1002 1.0000
16.000 1.4906 0.09718 0.09006 -0.0882 0.0946 1.0000
16.250 1.4866 0.10139 0.09431 -0.0892 0.0893 1.0000
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