GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 518 AIRFOIL (goe518-il) Reynolds number: 100,000 Max Cl/Cd: 39.15 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe518-il-100000-n5.txt Download as CSV file: xf-goe518-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 518 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
------ -------- --------- --------- -------- -------- --------
-10.250 0.0178 0.11195 0.10692 -0.0920 0.9187 0.0727
-10.000 0.0202 0.10870 0.10368 -0.0960 0.9137 0.0752
-9.750 0.0069 0.10569 0.10070 -0.1004 0.9060 0.0760
-9.500 0.0247 0.10199 0.09701 -0.1002 0.8999 0.0766
-9.250 0.0542 0.09836 0.09336 -0.1017 0.8965 0.0786
-9.000 0.0612 0.09575 0.09077 -0.1021 0.8881 0.0809
-8.750 0.0531 0.09234 0.08738 -0.1069 0.8803 0.0846
-8.500 0.0228 0.08959 0.08466 -0.1095 0.8672 0.0852
-8.250 0.0589 0.08540 0.08046 -0.1093 0.8642 0.0865
-8.000 0.0698 0.08261 0.07767 -0.1090 0.8565 0.0875
-7.750 0.0732 0.07966 0.07473 -0.1097 0.8478 0.0885
-7.500 0.0646 0.07720 0.07228 -0.1087 0.8368 0.0893
-7.000 0.0058 0.06512 0.05985 -0.1085 0.8129 0.0599
-6.750 0.0123 0.06266 0.05735 -0.1070 0.8039 0.0587
-6.500 0.0123 0.05949 0.05406 -0.1056 0.7943 0.0580
-6.250 0.0074 0.05683 0.05128 -0.1026 0.7825 0.0577
-5.750 -0.0099 0.04785 0.04144 -0.0957 0.7612 0.0536
-5.500 0.0116 0.04506 0.03845 -0.0956 0.7553 0.0532
-5.250 0.0118 0.04336 0.03660 -0.0914 0.7417 0.0530
-5.000 0.0235 0.04100 0.03397 -0.0892 0.7322 0.0527
-4.750 0.0370 0.03870 0.03137 -0.0869 0.7222 0.0525
-4.500 0.0480 0.03674 0.02910 -0.0841 0.7109 0.0524
-4.250 0.0699 0.03428 0.02612 -0.0829 0.7028 0.0531
-4.000 0.0827 0.03260 0.02399 -0.0800 0.6908 0.0536
-3.750 0.1097 0.03086 0.02190 -0.0795 0.6817 0.0539
-3.500 0.1332 0.02953 0.02029 -0.0784 0.6704 0.0540
-3.250 0.1590 0.02834 0.01886 -0.0777 0.6593 0.0544
-3.000 0.1928 0.02708 0.01730 -0.0784 0.6486 0.0548
-2.750 0.2158 0.02629 0.01631 -0.0772 0.6355 0.0553
-2.500 0.2441 0.02550 0.01531 -0.0770 0.6234 0.0561
-2.250 0.2760 0.02476 0.01434 -0.0774 0.6113 0.0575
-2.000 0.2972 0.02430 0.01371 -0.0759 0.5984 0.0591
-1.750 0.3234 0.02380 0.01299 -0.0752 0.5863 0.0602
-1.500 0.3490 0.02333 0.01241 -0.0746 0.5738 0.0611
-1.250 0.3678 0.02308 0.01212 -0.0728 0.5611 0.0619
-1.000 0.3893 0.02282 0.01178 -0.0715 0.5488 0.0632
-0.750 0.4097 0.02261 0.01148 -0.0699 0.5369 0.0646
-0.500 0.4274 0.02249 0.01128 -0.0679 0.5253 0.0663
-0.250 0.4485 0.02237 0.01104 -0.0665 0.5148 0.0689
0.000 0.4659 0.02236 0.01102 -0.0646 0.5040 0.0723
0.250 0.4865 0.02233 0.01086 -0.0631 0.4945 0.0763
0.500 0.5059 0.02234 0.01083 -0.0616 0.4850 0.0805
0.750 0.5277 0.02237 0.01077 -0.0604 0.4763 0.0878
1.000 0.5492 0.02243 0.01079 -0.0593 0.4674 0.1034
1.250 0.5767 0.02233 0.01075 -0.0594 0.4599 0.1567
1.750 0.7972 0.02207 0.01215 -0.0936 0.4365 1.0000
2.000 0.8134 0.02236 0.01229 -0.0916 0.4310 1.0000
2.250 0.8328 0.02266 0.01238 -0.0901 0.4263 1.0000
2.500 0.8493 0.02297 0.01260 -0.0882 0.4213 1.0000
2.750 0.8654 0.02330 0.01284 -0.0863 0.4163 1.0000
3.000 0.8828 0.02362 0.01304 -0.0846 0.4117 1.0000
3.250 0.9043 0.02395 0.01318 -0.0836 0.4078 1.0000
3.500 0.9204 0.02432 0.01350 -0.0817 0.4037 1.0000
3.750 0.9368 0.02470 0.01383 -0.0799 0.3996 1.0000
4.000 0.9550 0.02507 0.01413 -0.0784 0.3961 1.0000
4.250 0.9749 0.02544 0.01440 -0.0773 0.3929 1.0000
4.500 0.9986 0.02581 0.01463 -0.0768 0.3900 1.0000
4.750 1.0170 0.02624 0.01502 -0.0754 0.3871 1.0000
5.000 1.0325 0.02671 0.01550 -0.0736 0.3840 1.0000
5.250 1.0494 0.02718 0.01595 -0.0721 0.3811 1.0000
5.500 1.0675 0.02763 0.01637 -0.0708 0.3782 1.0000
5.750 1.0865 0.02806 0.01674 -0.0696 0.3754 1.0000
6.000 1.1086 0.02848 0.01708 -0.0690 0.3729 1.0000
6.250 1.1325 0.02893 0.01743 -0.0687 0.3705 1.0000
6.500 1.1430 0.02956 0.01814 -0.0663 0.3680 1.0000
6.750 1.1557 0.03019 0.01883 -0.0643 0.3655 1.0000
7.000 1.1703 0.03081 0.01949 -0.0626 0.3632 1.0000
7.250 1.1857 0.03143 0.02011 -0.0611 0.3608 1.0000
7.500 1.2033 0.03202 0.02071 -0.0600 0.3589 1.0000
7.750 1.2221 0.03258 0.02126 -0.0590 0.3569 1.0000
8.000 1.2437 0.03311 0.02176 -0.0586 0.3551 1.0000
8.250 1.2696 0.03359 0.02217 -0.0587 0.3533 1.0000
8.500 1.2758 0.03451 0.02320 -0.0561 0.3513 1.0000
8.750 1.2768 0.03559 0.02443 -0.0528 0.3490 1.0000
9.000 1.2805 0.03668 0.02563 -0.0501 0.3468 1.0000
9.250 1.2861 0.03778 0.02682 -0.0477 0.3447 1.0000
9.500 1.2940 0.03885 0.02797 -0.0458 0.3429 1.0000
9.750 1.3039 0.03986 0.02904 -0.0441 0.3410 1.0000
10.000 1.3175 0.04075 0.02997 -0.0429 0.3394 1.0000
10.250 1.3342 0.04154 0.03077 -0.0421 0.3378 1.0000
10.500 1.3570 0.04209 0.03132 -0.0420 0.3362 1.0000
10.750 1.3742 0.04295 0.03220 -0.0413 0.3346 1.0000
11.000 1.3372 0.04624 0.03579 -0.0352 0.3321 1.0000
11.250 1.2921 0.05072 0.04056 -0.0296 0.3291 1.0000
11.500 1.2265 0.05775 0.04790 -0.0243 0.3251 1.0000
11.750 1.1973 0.06272 0.05300 -0.0221 0.3217 1.0000
12.000 1.2141 0.06350 0.05380 -0.0217 0.3200 1.0000
12.250 1.2359 0.06390 0.05420 -0.0215 0.3188 1.0000
12.500 1.2698 0.06321 0.05350 -0.0217 0.3178 1.0000
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Polar data table (+)
Polar graphs
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