EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 562 AIRFOIL (e562-il) Reynolds number: 100,000 Max Cl/Cd: 49.28 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e562-il-100000.txt Download as CSV file: xf-e562-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 562 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3990 0.10904 0.10401 -0.0472 1.0000 0.0841
-10.750 -0.3930 0.10560 0.10056 -0.0465 1.0000 0.0807
-10.500 -0.5969 0.06661 0.06151 -0.0725 1.0000 0.0601
-10.250 -0.6231 0.06267 0.05757 -0.0724 1.0000 0.0596
-10.000 -0.6532 0.05935 0.05423 -0.0718 1.0000 0.0593
-9.750 -0.6751 0.05550 0.05026 -0.0719 1.0000 0.0589
-9.500 -0.6922 0.05175 0.04628 -0.0717 1.0000 0.0588
-9.250 -0.7024 0.04815 0.04233 -0.0716 1.0000 0.0593
-9.000 -0.7043 0.04475 0.03850 -0.0716 1.0000 0.0598
-8.750 -0.6991 0.04161 0.03492 -0.0716 1.0000 0.0604
-8.500 -0.6879 0.03831 0.03146 -0.0713 1.0000 0.0616
-8.250 -0.6734 0.03619 0.02925 -0.0707 1.0000 0.0634
-8.000 -0.6574 0.03451 0.02743 -0.0703 1.0000 0.0660
-7.750 -0.6397 0.03287 0.02549 -0.0700 1.0000 0.0696
-7.500 -0.6214 0.03094 0.02339 -0.0696 1.0000 0.0729
-7.250 -0.6033 0.02966 0.02216 -0.0689 1.0000 0.0768
-7.000 -0.5832 0.02856 0.02081 -0.0686 1.0000 0.0827
-6.750 -0.5645 0.02729 0.01972 -0.0682 1.0000 0.0900
-6.500 -0.5442 0.02610 0.01853 -0.0680 1.0000 0.0998
-6.250 -0.5091 0.02480 0.01731 -0.0708 0.9965 0.1247
-6.000 -0.4624 0.02365 0.01647 -0.0760 0.9896 0.1830
-5.750 -0.4158 0.02381 0.01675 -0.0806 0.9817 0.2325
-5.500 -0.3711 0.02442 0.01737 -0.0842 0.9730 0.2688
-5.250 -0.3313 0.02500 0.01798 -0.0866 0.9630 0.2975
-5.000 -0.2916 0.02533 0.01822 -0.0890 0.9533 0.3213
-4.750 -0.2498 0.02552 0.01837 -0.0916 0.9448 0.3416
-4.500 -0.2091 0.02567 0.01852 -0.0938 0.9358 0.3591
-4.250 -0.1728 0.02564 0.01841 -0.0953 0.9254 0.3749
-4.000 -0.1251 0.02548 0.01818 -0.0988 0.9194 0.3912
-3.750 -0.0913 0.02527 0.01785 -0.1000 0.9079 0.4056
-3.500 -0.0557 0.02516 0.01778 -0.1010 0.8982 0.4174
-3.250 -0.0117 0.02482 0.01740 -0.1036 0.8911 0.4315
-3.000 0.0228 0.02454 0.01706 -0.1047 0.8806 0.4443
-2.750 0.0705 0.02396 0.01638 -0.1080 0.8750 0.4588
-2.500 0.1061 0.02358 0.01588 -0.1094 0.8646 0.4719
-2.250 0.1538 0.02296 0.01528 -0.1123 0.8595 0.4841
-2.000 0.1906 0.02255 0.01483 -0.1136 0.8495 0.4955
-1.750 0.2413 0.02188 0.01409 -0.1174 0.8438 0.5096
-1.500 0.2793 0.02148 0.01361 -0.1191 0.8333 0.5228
-1.250 0.3274 0.02088 0.01299 -0.1222 0.8266 0.5359
-1.000 0.3600 0.02061 0.01273 -0.1227 0.8144 0.5471
-0.750 0.3995 0.02023 0.01229 -0.1245 0.8042 0.5603
-0.500 0.4403 0.01986 0.01184 -0.1265 0.7940 0.5741
-0.250 0.4703 0.01974 0.01170 -0.1266 0.7807 0.5867
0.000 0.5008 0.01961 0.01158 -0.1267 0.7682 0.5985
0.250 0.5349 0.01944 0.01136 -0.1275 0.7570 0.6117
0.500 0.5671 0.01933 0.01119 -0.1279 0.7450 0.6255
0.750 0.5936 0.01936 0.01120 -0.1275 0.7317 0.6393
1.000 0.6207 0.01938 0.01123 -0.1271 0.7193 0.6532
1.250 0.6502 0.01935 0.01118 -0.1270 0.7083 0.6675
1.500 0.6776 0.01936 0.01119 -0.1266 0.6966 0.6824
1.750 0.7012 0.01948 0.01135 -0.1256 0.6843 0.6979
2.000 0.7276 0.01955 0.01143 -0.1251 0.6734 0.7148
2.250 0.7562 0.01957 0.01143 -0.1248 0.6632 0.7337
2.500 0.7775 0.01974 0.01168 -0.1235 0.6514 0.7535
2.750 0.8012 0.01982 0.01181 -0.1223 0.6414 0.7744
3.000 0.8256 0.01988 0.01189 -0.1212 0.6315 0.8002
3.250 0.8426 0.02001 0.01214 -0.1188 0.6210 0.8289
3.500 0.8648 0.01991 0.01206 -0.1170 0.6129 0.8685
3.750 0.8804 0.01983 0.01220 -0.1143 0.6021 0.9442
4.000 0.9235 0.02015 0.01241 -0.1183 0.5913 1.0000
4.250 0.9600 0.02046 0.01257 -0.1204 0.5819 1.0000
4.500 0.9855 0.02096 0.01308 -0.1204 0.5712 1.0000
4.750 1.0173 0.02131 0.01331 -0.1212 0.5626 1.0000
5.000 1.0417 0.02177 0.01379 -0.1208 0.5524 1.0000
5.250 1.0682 0.02224 0.01424 -0.1207 0.5434 1.0000
5.500 1.0961 0.02262 0.01458 -0.1207 0.5344 1.0000
5.750 1.1189 0.02318 0.01520 -0.1200 0.5249 1.0000
6.000 1.1497 0.02349 0.01542 -0.1204 0.5166 1.0000
6.250 1.1691 0.02413 0.01619 -0.1191 0.5067 1.0000
6.500 1.2007 0.02445 0.01641 -0.1196 0.4988 1.0000
6.750 1.2188 0.02508 0.01719 -0.1181 0.4887 1.0000
7.000 1.2453 0.02554 0.01763 -0.1178 0.4802 1.0000
7.250 1.2683 0.02601 0.01817 -0.1170 0.4707 1.0000
7.500 1.2899 0.02659 0.01883 -0.1160 0.4614 1.0000
7.750 1.3188 0.02688 0.01907 -0.1160 0.4524 1.0000
8.000 1.3351 0.02755 0.01991 -0.1141 0.4422 1.0000
8.250 1.3633 0.02787 0.02018 -0.1141 0.4332 1.0000
8.500 1.3816 0.02837 0.02080 -0.1124 0.4227 1.0000
8.750 1.4010 0.02892 0.02144 -0.1111 0.4127 1.0000
9.000 1.4321 0.02906 0.02147 -0.1113 0.4029 1.0000
9.250 1.4425 0.02970 0.02234 -0.1085 0.3918 1.0000
9.500 1.4611 0.03016 0.02286 -0.1070 0.3811 1.0000
9.750 1.4873 0.03032 0.02295 -0.1065 0.3703 1.0000
10.000 1.4983 0.03084 0.02364 -0.1037 0.3588 1.0000
10.250 1.5107 0.03138 0.02429 -0.1013 0.3474 1.0000
10.500 1.5276 0.03172 0.02464 -0.0994 0.3359 1.0000
10.750 1.5464 0.03196 0.02482 -0.0978 0.3239 1.0000
11.000 1.5480 0.03264 0.02568 -0.0938 0.3121 1.0000
11.250 1.5506 0.03328 0.02644 -0.0900 0.3006 1.0000
11.500 1.5554 0.03386 0.02704 -0.0865 0.2889 1.0000
11.750 1.5604 0.03447 0.02761 -0.0832 0.2768 1.0000
12.000 1.5558 0.03547 0.02873 -0.0789 0.2650 1.0000
12.250 1.5504 0.03673 0.03010 -0.0750 0.2530 1.0000
12.500 1.5460 0.03811 0.03153 -0.0715 0.2409 1.0000
12.750 1.5414 0.03968 0.03310 -0.0684 0.2287 1.0000
13.000 1.5364 0.04145 0.03484 -0.0657 0.2164 1.0000
13.250 1.5278 0.04368 0.03713 -0.0631 0.2044 1.0000
13.500 1.5174 0.04635 0.03989 -0.0609 0.1926 1.0000
13.750 1.5083 0.04919 0.04277 -0.0593 0.1811 1.0000
14.000 1.4998 0.05218 0.04575 -0.0579 0.1701 1.0000
14.250 1.4931 0.05519 0.04866 -0.0569 0.1593 1.0000
14.500 1.4808 0.05901 0.05262 -0.0564 0.1495 1.0000
14.750 1.4718 0.06274 0.05639 -0.0560 0.1399 1.0000
15.000 1.4661 0.06619 0.05975 -0.0558 0.1306 1.0000
15.250 1.4555 0.07043 0.06411 -0.0561 0.1225 1.0000
15.500 1.4488 0.07441 0.06811 -0.0563 0.1144 1.0000
15.750 1.4493 0.07741 0.07092 -0.0562 0.1057 1.0000
16.000 1.4354 0.08267 0.07648 -0.0574 0.1001 1.0000
16.250 1.4385 0.08549 0.07912 -0.0573 0.0925 1.0000
16.500 1.4256 0.09089 0.08480 -0.0589 0.0879 1.0000
16.750 1.4333 0.09310 0.08679 -0.0586 0.0809 1.0000
17.000 1.4189 0.09895 0.09298 -0.0607 0.0777 1.0000
17.250 1.4140 0.10331 0.09746 -0.0621 0.0735 1.0000
17.500 1.4199 0.10598 0.10005 -0.0622 0.0687 1.0000
17.750 1.4055 0.11212 0.10648 -0.0649 0.0664 1.0000
18.000 1.3967 0.11740 0.11195 -0.0672 0.0638 1.0000
18.250 1.4139 0.11813 0.11244 -0.0662 0.0591 1.0000
18.500 1.3954 0.12521 0.11984 -0.0700 0.0582 1.0000
18.750 1.3763 0.13269 0.12762 -0.0743 0.0573 1.0000
19.000 1.3547 0.14093 0.13613 -0.0794 0.0567 1.0000
19.250 1.3272 0.15078 0.14626 -0.0858 0.0567 1.0000
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Polar data table (+)
Polar graphs
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