GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 359 AIRFOIL (goe359-il) Reynolds number: 100,000 Max Cl/Cd: 63 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe359-il-100000-n5.txt Download as CSV file: xf-goe359-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 359 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2493 0.09787 0.09350 -0.0282 1.0000 0.0310
-7.250 -0.2535 0.09612 0.09187 -0.0268 1.0000 0.0315
-7.000 -0.2629 0.09489 0.09076 -0.0245 1.0000 0.0318
-6.750 -0.2492 0.09162 0.08753 -0.0283 0.9931 0.0332
-6.500 -0.2181 0.08771 0.08361 -0.0388 0.9786 0.0372
-6.250 -0.1798 0.08408 0.07991 -0.0532 0.9600 0.0382
-6.000 -0.1455 0.07956 0.07531 -0.0624 0.9465 0.0384
-5.750 -0.1109 0.07468 0.07032 -0.0704 0.9353 0.0385
-5.500 -0.0874 0.06878 0.06442 -0.0742 0.9261 0.0391
-5.250 -0.0713 0.06462 0.06026 -0.0738 0.9155 0.0406
-5.000 -0.0438 0.06111 0.05668 -0.0773 0.9050 0.0447
-4.500 0.0358 0.05215 0.04736 -0.0934 0.8826 0.0529
-4.250 0.0633 0.04900 0.04408 -0.0960 0.8703 0.0562
-4.000 0.0989 0.04552 0.04039 -0.1012 0.8582 0.0661
-3.750 0.1291 0.04293 0.03763 -0.1041 0.8463 0.0792
-3.500 0.1728 0.03789 0.03211 -0.1093 0.8359 0.0604
-3.250 0.2052 0.03459 0.02851 -0.1117 0.8241 0.0586
-3.000 0.2384 0.03139 0.02489 -0.1137 0.8123 0.0567
-2.750 0.2773 0.02737 0.01996 -0.1158 0.8017 0.0515
-2.500 0.3034 0.02608 0.01863 -0.1163 0.7900 0.0553
-2.250 0.3334 0.02440 0.01655 -0.1167 0.7788 0.0569
-2.000 0.3632 0.02266 0.01433 -0.1169 0.7669 0.0555
-1.750 0.3925 0.02129 0.01253 -0.1169 0.7555 0.0549
-1.500 0.4212 0.02022 0.01109 -0.1168 0.7443 0.0550
-1.250 0.4496 0.01936 0.00994 -0.1166 0.7334 0.0556
-1.000 0.4770 0.01867 0.00903 -0.1163 0.7216 0.0565
-0.750 0.5043 0.01822 0.00840 -0.1160 0.7103 0.0604
-0.500 0.5316 0.01779 0.00778 -0.1156 0.6996 0.0624
-0.250 0.5587 0.01735 0.00720 -0.1152 0.6893 0.0626
0.000 0.5853 0.01700 0.00678 -0.1148 0.6779 0.0628
0.250 0.6118 0.01672 0.00644 -0.1143 0.6676 0.0633
0.500 0.6384 0.01651 0.00611 -0.1139 0.6583 0.0643
0.750 0.6652 0.01641 0.00591 -0.1135 0.6477 0.0658
1.000 0.6922 0.01636 0.00578 -0.1132 0.6372 0.0682
1.250 0.7192 0.01635 0.00567 -0.1128 0.6269 0.0721
1.500 0.7460 0.01634 0.00564 -0.1125 0.6164 0.0833
1.750 0.7723 0.01595 0.00579 -0.1124 0.6048 0.3015
2.250 0.8232 0.01500 0.00581 -0.1110 0.5823 1.0000
2.750 0.8744 0.01542 0.00599 -0.1100 0.5592 1.0000
3.000 0.9001 0.01565 0.00614 -0.1095 0.5491 1.0000
3.500 0.9517 0.01614 0.00653 -0.1087 0.5316 1.0000
3.750 0.9773 0.01639 0.00676 -0.1083 0.5229 1.0000
4.000 1.0027 0.01665 0.00700 -0.1078 0.5138 1.0000
4.250 1.0279 0.01692 0.00728 -0.1074 0.5044 1.0000
4.500 1.0533 0.01719 0.00755 -0.1069 0.4962 1.0000
4.750 1.0781 0.01748 0.00789 -0.1064 0.4862 1.0000
5.000 1.1025 0.01776 0.00821 -0.1058 0.4754 1.0000
5.250 1.1266 0.01805 0.00853 -0.1051 0.4635 1.0000
5.500 1.1502 0.01834 0.00884 -0.1044 0.4508 1.0000
5.750 1.1734 0.01865 0.00917 -0.1036 0.4373 1.0000
6.000 1.1944 0.01896 0.00950 -0.1024 0.4139 1.0000
6.250 1.2135 0.01933 0.00981 -0.1009 0.3824 1.0000
6.500 1.2329 0.01978 0.01019 -0.0996 0.3507 1.0000
6.750 1.2512 0.02036 0.01064 -0.0982 0.3120 1.0000
7.000 1.2665 0.02122 0.01122 -0.0965 0.2705 1.0000
7.250 1.2816 0.02219 0.01198 -0.0948 0.2392 1.0000
7.500 1.2953 0.02331 0.01289 -0.0931 0.2062 1.0000
7.750 1.3083 0.02448 0.01389 -0.0913 0.1598 1.0000
8.000 1.3130 0.02632 0.01523 -0.0886 0.0989 1.0000
8.250 1.3147 0.02836 0.01691 -0.0854 0.0513 1.0000
8.500 1.3230 0.02974 0.01828 -0.0830 0.0245 1.0000
8.750 1.3281 0.03121 0.01973 -0.0801 0.0214 1.0000
9.000 1.3370 0.03244 0.02110 -0.0779 0.0200 1.0000
9.250 1.3451 0.03376 0.02258 -0.0757 0.0192 1.0000
9.500 1.3513 0.03529 0.02433 -0.0735 0.0185 1.0000
9.750 1.3553 0.03707 0.02638 -0.0714 0.0176 1.0000
10.000 1.3572 0.03914 0.02868 -0.0695 0.0168 1.0000
10.250 1.3575 0.04148 0.03124 -0.0679 0.0162 1.0000
10.500 1.3568 0.04404 0.03402 -0.0665 0.0158 1.0000
10.750 1.3544 0.04691 0.03711 -0.0654 0.0156 1.0000
11.000 1.3503 0.05012 0.04054 -0.0647 0.0154 1.0000
11.250 1.3447 0.05367 0.04430 -0.0643 0.0152 1.0000
11.500 1.3375 0.05756 0.04839 -0.0641 0.0150 1.0000
11.750 1.3294 0.06173 0.05277 -0.0643 0.0149 1.0000
12.000 1.3204 0.06618 0.05740 -0.0648 0.0148 1.0000
12.250 1.3108 0.07082 0.06223 -0.0654 0.0147 1.0000
12.500 1.3010 0.07558 0.06716 -0.0662 0.0147 1.0000
12.750 1.2915 0.08042 0.07217 -0.0671 0.0146 1.0000
13.000 1.2827 0.08525 0.07714 -0.0680 0.0145 1.0000
13.250 1.2751 0.08987 0.08190 -0.0689 0.0144 1.0000
13.500 1.2693 0.09414 0.08628 -0.0695 0.0142 1.0000
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Polar data table (+)
Polar graphs
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