GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 264 AIRFOIL (goe264-il) Reynolds number: 100,000 Max Cl/Cd: 60.82 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe264-il-100000-n5.txt Download as CSV file: xf-goe264-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 264 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3018 0.10233 0.09771 -0.0260 1.0000 0.0414
-7.500 -0.3027 0.10076 0.09623 -0.0276 1.0000 0.0416
-7.250 -0.3017 0.09880 0.09433 -0.0292 1.0000 0.0418
-7.000 -0.2995 0.09658 0.09218 -0.0307 1.0000 0.0419
-6.750 -0.2960 0.09412 0.08976 -0.0321 1.0000 0.0419
-6.500 -0.2913 0.09144 0.08711 -0.0333 1.0000 0.0420
-6.250 -0.2855 0.08860 0.08429 -0.0345 1.0000 0.0420
-5.750 -0.2566 0.07896 0.07469 -0.0335 0.9920 0.0462
-5.500 -0.2193 0.07478 0.07042 -0.0424 0.9857 0.0514
-5.250 -0.1561 0.07037 0.06574 -0.0605 0.9776 0.0539
-4.750 -0.1061 0.06078 0.05613 -0.0661 0.9659 0.0586
-4.500 -0.0670 0.05683 0.05204 -0.0727 0.9584 0.0625
-4.000 0.0164 0.04926 0.04415 -0.0860 0.9430 0.0749
-3.750 0.0684 0.04419 0.03872 -0.0944 0.9369 0.0647
-3.500 0.1181 0.04061 0.03469 -0.1011 0.9266 0.0678
-3.250 0.1476 0.03753 0.03152 -0.1031 0.9162 0.0649
-3.000 0.1873 0.03437 0.02808 -0.1068 0.9067 0.0631
-2.750 0.2245 0.03162 0.02503 -0.1096 0.8944 0.0627
-2.500 0.2628 0.02916 0.02214 -0.1121 0.8815 0.0665
-2.250 0.2972 0.02694 0.01960 -0.1138 0.8678 0.0658
-2.000 0.3313 0.02486 0.01716 -0.1151 0.8534 0.0652
-1.750 0.3645 0.02298 0.01490 -0.1161 0.8381 0.0652
-1.500 0.3967 0.02133 0.01282 -0.1166 0.8219 0.0658
-1.250 0.4272 0.01999 0.01107 -0.1168 0.8037 0.0670
-1.000 0.4566 0.01898 0.00970 -0.1167 0.7843 0.0685
-0.750 0.4839 0.01851 0.00916 -0.1165 0.7639 0.0724
-0.500 0.5116 0.01806 0.00855 -0.1162 0.7422 0.0765
-0.250 0.5395 0.01743 0.00767 -0.1158 0.7209 0.0784
0.000 0.5671 0.01691 0.00693 -0.1153 0.6998 0.0807
0.250 0.5940 0.01653 0.00639 -0.1148 0.6798 0.0834
0.500 0.6209 0.01631 0.00608 -0.1144 0.6613 0.0873
0.750 0.6473 0.01617 0.00580 -0.1139 0.6439 0.0939
1.000 0.6739 0.01614 0.00571 -0.1134 0.6272 0.1038
1.250 0.7009 0.01609 0.00555 -0.1130 0.6116 0.1141
1.500 0.7280 0.01607 0.00546 -0.1128 0.5966 0.1305
1.750 0.7553 0.01609 0.00546 -0.1126 0.5820 0.1594
2.000 0.7826 0.01612 0.00554 -0.1125 0.5679 0.2015
2.250 0.8100 0.01611 0.00564 -0.1126 0.5542 0.2682
2.500 0.8292 0.01493 0.00566 -0.1105 0.5418 1.0000
2.750 0.8562 0.01519 0.00577 -0.1103 0.5286 1.0000
3.000 0.8831 0.01547 0.00594 -0.1101 0.5160 1.0000
3.250 0.9099 0.01575 0.00615 -0.1099 0.5039 1.0000
3.500 0.9365 0.01605 0.00637 -0.1097 0.4926 1.0000
3.750 0.9630 0.01637 0.00660 -0.1094 0.4823 1.0000
4.000 0.9897 0.01668 0.00694 -0.1092 0.4718 1.0000
4.250 1.0162 0.01702 0.00726 -0.1090 0.4623 1.0000
4.500 1.0424 0.01738 0.00759 -0.1088 0.4535 1.0000
4.750 1.0688 0.01774 0.00799 -0.1086 0.4443 1.0000
5.000 1.0950 0.01814 0.00841 -0.1083 0.4369 1.0000
5.250 1.1213 0.01853 0.00890 -0.1081 0.4289 1.0000
5.500 1.1473 0.01896 0.00934 -0.1079 0.4225 1.0000
5.750 1.1733 0.01938 0.00990 -0.1076 0.4145 1.0000
6.000 1.1990 0.01983 0.01042 -0.1073 0.4077 1.0000
6.250 1.2244 0.02026 0.01103 -0.1070 0.3992 1.0000
6.500 1.2497 0.02071 0.01158 -0.1066 0.3918 1.0000
6.750 1.2728 0.02103 0.01202 -0.1058 0.3756 1.0000
7.000 1.2925 0.02125 0.01230 -0.1045 0.3447 1.0000
7.250 1.3124 0.02165 0.01272 -0.1033 0.3117 1.0000
7.500 1.3315 0.02226 0.01332 -0.1021 0.2701 1.0000
7.750 1.3324 0.02499 0.01491 -0.0991 0.1112 1.0000
8.000 1.3344 0.02799 0.01741 -0.0962 0.0468 1.0000
8.500 1.3540 0.03142 0.02118 -0.0915 0.0328 1.0000
8.750 1.3599 0.03318 0.02310 -0.0889 0.0294 1.0000
9.000 1.3619 0.03504 0.02518 -0.0858 0.0273 1.0000
9.250 1.3615 0.03680 0.02716 -0.0824 0.0260 1.0000
9.500 1.3593 0.03889 0.02945 -0.0793 0.0250 1.0000
9.750 1.3565 0.04124 0.03197 -0.0767 0.0242 1.0000
10.000 1.3537 0.04377 0.03466 -0.0745 0.0233 1.0000
10.250 1.3519 0.04642 0.03744 -0.0727 0.0223 1.0000
10.500 1.3509 0.04913 0.04026 -0.0713 0.0213 1.0000
10.750 1.3501 0.05194 0.04315 -0.0700 0.0202 1.0000
11.000 1.3498 0.05481 0.04607 -0.0685 0.0192 1.0000
11.250 1.3554 0.05742 0.04870 -0.0660 0.0184 1.0000
11.500 1.3649 0.05972 0.05112 -0.0643 0.0180 1.0000
11.750 1.3746 0.06214 0.05374 -0.0628 0.0176 1.0000
12.000 1.3833 0.06483 0.05663 -0.0613 0.0173 1.0000
12.250 1.3876 0.06791 0.06002 -0.0602 0.0169 1.0000
12.500 1.3885 0.07129 0.06366 -0.0595 0.0165 1.0000
12.750 1.3863 0.07498 0.06761 -0.0591 0.0160 1.0000
13.000 1.3817 0.07899 0.07188 -0.0590 0.0156 1.0000
13.250 1.3750 0.08334 0.07649 -0.0593 0.0152 1.0000
13.500 1.3664 0.08806 0.08146 -0.0601 0.0150 1.0000
13.750 1.3558 0.09320 0.08684 -0.0613 0.0148 1.0000
14.000 1.3436 0.09870 0.09260 -0.0630 0.0148 1.0000
14.250 1.3301 0.10465 0.09879 -0.0653 0.0148 1.0000
14.500 1.3157 0.11105 0.10543 -0.0682 0.0148 1.0000
14.750 1.3005 0.11792 0.11253 -0.0717 0.0148 1.0000
15.000 1.2848 0.12529 0.12012 -0.0759 0.0149 1.0000
15.250 1.2689 0.13322 0.12824 -0.0807 0.0150 1.0000
15.500 1.2525 0.14179 0.13701 -0.0863 0.0151 1.0000
15.750 1.2359 0.15110 0.14648 -0.0925 0.0153 1.0000
16.000 1.2190 0.16130 0.15683 -0.0995 0.0155 1.0000
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Polar data table (+)
Polar graphs
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