GOE 679 AIRFOIL (goe679-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 679 AIRFOIL (goe679-il) Reynolds number: 100,000 Max Cl/Cd: 42.67 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe679-il-100000.txt Download as CSV file: xf-goe679-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 679 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4029 0.12029 0.11577 -0.0278 0.9971 0.1652
-8.750 -0.5413 0.07982 0.07512 -0.0492 0.9918 0.1057
-8.500 -0.5960 0.06837 0.06337 -0.0549 0.9812 0.1030
-8.250 -0.6467 0.05712 0.05146 -0.0568 0.9697 0.1016
-8.000 -0.6592 0.05076 0.04447 -0.0564 0.9595 0.1021
-7.750 -0.6541 0.04606 0.03909 -0.0564 0.9514 0.1034
-7.500 -0.6426 0.04253 0.03487 -0.0558 0.9427 0.1054
-7.250 -0.6130 0.04176 0.03424 -0.0566 0.9343 0.1079
-7.000 -0.5806 0.04048 0.03279 -0.0581 0.9268 0.1119
-6.750 -0.5641 0.03863 0.03050 -0.0570 0.9174 0.1159
-6.500 -0.5236 0.03803 0.03002 -0.0594 0.9108 0.1212
-6.250 -0.5066 0.03659 0.02820 -0.0579 0.9008 0.1267
-6.000 -0.4657 0.03598 0.02767 -0.0602 0.8946 0.1349
-5.750 -0.4454 0.03541 0.02711 -0.0590 0.8842 0.1426
-5.500 -0.4057 0.03472 0.02640 -0.0609 0.8779 0.1557
-5.250 -0.3868 0.03423 0.02578 -0.0594 0.8671 0.1672
-5.000 -0.3460 0.03372 0.02526 -0.0614 0.8608 0.1823
-4.750 -0.3242 0.03366 0.02526 -0.0602 0.8498 0.1927
-4.500 -0.2832 0.03315 0.02479 -0.0621 0.8434 0.2060
-4.250 -0.2603 0.03279 0.02432 -0.0611 0.8328 0.2169
-4.000 -0.2213 0.03241 0.02389 -0.0626 0.8257 0.2305
-3.750 -0.1708 0.03160 0.02320 -0.0658 0.8222 0.2449
-3.500 -0.1571 0.03135 0.02282 -0.0632 0.8082 0.2535
-3.250 -0.1076 0.03032 0.02181 -0.0662 0.8045 0.2662
-3.000 -0.0894 0.02992 0.02130 -0.0643 0.7917 0.2738
-2.750 -0.0412 0.02873 0.02011 -0.0669 0.7873 0.2848
-2.500 0.0147 0.02727 0.01856 -0.0709 0.7845 0.2971
-2.250 0.0331 0.02702 0.01830 -0.0689 0.7710 0.3053
-2.000 0.0899 0.02568 0.01691 -0.0732 0.7668 0.3192
-1.750 0.1606 0.02432 0.01547 -0.0802 0.7638 0.3372
-1.500 0.1754 0.02410 0.01532 -0.0773 0.7488 0.3475
-1.250 0.2460 0.02285 0.01407 -0.0845 0.7439 0.3706
-1.000 0.2625 0.02266 0.01391 -0.0820 0.7291 0.3846
-0.750 0.3187 0.02177 0.01306 -0.0866 0.7210 0.4124
-0.500 0.3395 0.02149 0.01288 -0.0849 0.7071 0.4349
-0.250 0.3673 0.02117 0.01264 -0.0844 0.6948 0.4662
0.000 0.4098 0.02047 0.01216 -0.0865 0.6845 0.5161
0.250 0.4265 0.02022 0.01225 -0.0840 0.6711 0.5793
0.500 0.5389 0.01947 0.01244 -0.0979 0.6580 0.8749
0.750 0.6581 0.01981 0.01241 -0.1138 0.6427 0.9554
1.000 0.7493 0.02006 0.01242 -0.1258 0.6256 0.9907
1.250 0.7871 0.02015 0.01236 -0.1282 0.6120 1.0000
1.500 0.8103 0.02017 0.01214 -0.1275 0.6024 1.0000
1.750 0.8143 0.02040 0.01233 -0.1233 0.5912 1.0000
2.000 0.8372 0.02051 0.01223 -0.1223 0.5820 1.0000
2.250 0.8443 0.02079 0.01246 -0.1186 0.5716 1.0000
2.500 0.8699 0.02096 0.01243 -0.1181 0.5629 1.0000
2.750 0.8758 0.02131 0.01278 -0.1141 0.5533 1.0000
3.000 0.9072 0.02149 0.01271 -0.1146 0.5448 1.0000
3.250 0.9086 0.02193 0.01320 -0.1097 0.5356 1.0000
3.500 0.9360 0.02216 0.01324 -0.1096 0.5272 1.0000
3.750 0.9440 0.02262 0.01371 -0.1059 0.5186 1.0000
4.000 0.9641 0.02293 0.01391 -0.1044 0.5101 1.0000
4.250 0.9835 0.02336 0.01424 -0.1028 0.5022 1.0000
4.500 0.9934 0.02379 0.01467 -0.0994 0.4936 1.0000
4.750 1.0287 0.02411 0.01476 -0.1007 0.4858 1.0000
5.000 1.0266 0.02467 0.01545 -0.0953 0.4777 1.0000
5.250 1.0508 0.02501 0.01566 -0.0945 0.4698 1.0000
5.500 1.0658 0.02556 0.01618 -0.0922 0.4622 1.0000
5.750 1.0753 0.02604 0.01668 -0.0888 0.4542 1.0000
6.000 1.1136 0.02641 0.01681 -0.0907 0.4467 1.0000
6.250 1.1071 0.02708 0.01765 -0.0846 0.4391 1.0000
6.500 1.1279 0.02749 0.01798 -0.0833 0.4318 1.0000
6.750 1.1494 0.02806 0.01848 -0.0822 0.4247 1.0000
7.000 1.1501 0.02870 0.01921 -0.0774 0.4173 1.0000
7.250 1.1817 0.02903 0.01939 -0.0781 0.4104 1.0000
7.500 1.1865 0.02981 0.02023 -0.0742 0.4037 1.0000
7.750 1.1912 0.03047 0.02096 -0.0703 0.3971 1.0000
8.000 1.2283 0.03084 0.02116 -0.0719 0.3908 1.0000
8.250 1.2270 0.03178 0.02222 -0.0671 0.3850 1.0000
8.500 1.2260 0.03258 0.02310 -0.0624 0.3789 1.0000
8.750 1.2589 0.03292 0.02331 -0.0634 0.3730 1.0000
9.000 1.2678 0.03381 0.02424 -0.0604 0.3677 1.0000
9.250 1.2526 0.03484 0.02543 -0.0536 0.3625 1.0000
9.500 1.2657 0.03551 0.02611 -0.0514 0.3574 1.0000
9.750 1.3237 0.03589 0.02626 -0.0566 0.3523 1.0000
10.000 1.2898 0.03741 0.02804 -0.0472 0.3484 1.0000
10.250 1.2732 0.03895 0.02975 -0.0411 0.3440 1.0000
10.500 1.2835 0.03983 0.03067 -0.0389 0.3395 1.0000
10.750 1.3394 0.03973 0.03037 -0.0430 0.3349 1.0000
11.000 1.3092 0.04188 0.03275 -0.0356 0.3314 1.0000
11.250 1.2645 0.04496 0.03610 -0.0276 0.3276 1.0000
11.500 1.2410 0.04774 0.03902 -0.0230 0.3237 1.0000
11.750 1.2651 0.04828 0.03956 -0.0227 0.3202 1.0000
12.000 1.3510 0.04664 0.03766 -0.0285 0.3165 1.0000
12.250 0.6865 0.13009 0.12236 -0.0293 0.3163 1.0000
12.500 0.5845 0.14442 0.13685 -0.0362 0.3425 1.0000
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Polar data table (+)
Polar graphs
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