FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il) Reynolds number: 100,000 Max Cl/Cd: 62.5 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx601001-il-100000-n5.txt Download as CSV file: xf-fx601001-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-100 (126) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3899 0.08981 0.08491 -0.0417 1.0000 0.0221
-9.000 -0.3918 0.08605 0.08123 -0.0425 1.0000 0.0219
-8.750 -0.3960 0.08207 0.07732 -0.0435 1.0000 0.0218
-8.500 -0.4021 0.07815 0.07349 -0.0443 1.0000 0.0216
-8.250 -0.4116 0.07418 0.06963 -0.0449 1.0000 0.0215
-8.000 -0.4255 0.07030 0.06586 -0.0449 1.0000 0.0213
-7.750 -0.4400 0.06541 0.06106 -0.0465 1.0000 0.0211
-7.500 -0.4544 0.05954 0.05522 -0.0511 1.0000 0.0209
-7.250 -0.4622 0.05347 0.04902 -0.0576 1.0000 0.0207
-7.000 -0.4624 0.04767 0.04294 -0.0627 1.0000 0.0205
-6.750 -0.4502 0.04173 0.03652 -0.0681 0.9994 0.0205
-6.500 -0.4114 0.03501 0.02897 -0.0768 0.9943 0.0207
-6.250 -0.3727 0.03024 0.02341 -0.0821 0.9897 0.0213
-6.000 -0.3345 0.02707 0.01971 -0.0859 0.9857 0.0228
-5.750 -0.2990 0.02535 0.01771 -0.0886 0.9804 0.0252
-5.500 -0.2615 0.02337 0.01543 -0.0910 0.9768 0.0273
-5.250 -0.2281 0.02175 0.01356 -0.0924 0.9712 0.0299
-5.000 -0.1910 0.02070 0.01246 -0.0947 0.9668 0.0354
-4.750 -0.1567 0.01964 0.01131 -0.0964 0.9611 0.0440
-4.500 -0.1198 0.01865 0.01019 -0.0986 0.9560 0.0631
-4.250 -0.0814 0.01780 0.00934 -0.1014 0.9519 0.0912
-4.000 -0.0479 0.01705 0.00868 -0.1031 0.9449 0.1211
-3.750 -0.0085 0.01612 0.00797 -0.1062 0.9405 0.1807
-3.500 0.0269 0.01529 0.00751 -0.1084 0.9345 0.2947
-3.250 0.0603 0.01519 0.00777 -0.1094 0.9278 0.4023
-3.000 0.0941 0.01532 0.00773 -0.1103 0.9208 0.4488
-2.750 0.1278 0.01545 0.00766 -0.1112 0.9134 0.4799
-2.500 0.1588 0.01563 0.00777 -0.1114 0.9053 0.5113
-2.250 0.1912 0.01568 0.00775 -0.1119 0.8981 0.5362
-2.000 0.2212 0.01564 0.00762 -0.1121 0.8893 0.5502
-1.750 0.2548 0.01550 0.00741 -0.1129 0.8825 0.5595
-1.500 0.2842 0.01541 0.00724 -0.1130 0.8726 0.5673
-1.250 0.3157 0.01530 0.00704 -0.1135 0.8641 0.5750
-1.000 0.3472 0.01518 0.00686 -0.1140 0.8556 0.5820
-0.750 0.3765 0.01513 0.00677 -0.1140 0.8453 0.5912
-0.500 0.4062 0.01506 0.00668 -0.1141 0.8358 0.6000
-0.250 0.4373 0.01498 0.00655 -0.1145 0.8267 0.6085
0.000 0.4655 0.01494 0.00650 -0.1143 0.8153 0.6136
0.250 0.4948 0.01490 0.00643 -0.1144 0.8043 0.6188
0.500 0.5241 0.01485 0.00634 -0.1145 0.7925 0.6238
0.750 0.5523 0.01479 0.00627 -0.1142 0.7786 0.6284
1.000 0.5805 0.01475 0.00620 -0.1139 0.7639 0.6336
1.250 0.6085 0.01475 0.00617 -0.1137 0.7499 0.6388
1.500 0.6365 0.01475 0.00619 -0.1135 0.7372 0.6438
1.750 0.6646 0.01479 0.00621 -0.1133 0.7243 0.6495
2.000 0.6919 0.01483 0.00628 -0.1130 0.7107 0.6552
2.500 0.7461 0.01493 0.00642 -0.1122 0.6799 0.6684
2.750 0.7723 0.01499 0.00650 -0.1116 0.6609 0.6756
3.000 0.7987 0.01507 0.00660 -0.1110 0.6427 0.6841
3.250 0.8251 0.01518 0.00676 -0.1105 0.6264 0.6942
3.500 0.8513 0.01529 0.00695 -0.1100 0.6108 0.7052
3.750 0.8772 0.01542 0.00714 -0.1094 0.5949 0.7185
4.000 0.9025 0.01554 0.00740 -0.1088 0.5777 0.7362
4.250 0.9269 0.01565 0.00765 -0.1079 0.5599 0.7607
4.500 0.9495 0.01569 0.00789 -0.1066 0.5419 0.8018
4.750 0.9711 0.01567 0.00807 -0.1050 0.5223 1.0000
5.000 0.9969 0.01600 0.00842 -0.1046 0.4984 1.0000
5.250 1.0219 0.01635 0.00883 -0.1041 0.4718 1.0000
5.500 1.0462 0.01675 0.00923 -0.1034 0.4419 1.0000
5.750 1.0689 0.01725 0.00963 -0.1025 0.4064 1.0000
6.000 1.0904 0.01788 0.01012 -0.1014 0.3692 1.0000
6.250 1.1115 0.01860 0.01073 -0.1004 0.3374 1.0000
6.500 1.1323 0.01938 0.01142 -0.0994 0.3078 1.0000
6.750 1.1512 0.02026 0.01223 -0.0981 0.2689 1.0000
7.000 1.1691 0.02121 0.01300 -0.0969 0.2266 1.0000
7.250 1.1865 0.02224 0.01383 -0.0957 0.1869 1.0000
7.500 1.2028 0.02343 0.01479 -0.0943 0.1395 1.0000
7.750 1.2147 0.02516 0.01606 -0.0926 0.0750 1.0000
8.000 1.2247 0.02722 0.01782 -0.0905 0.0406 1.0000
8.250 1.2368 0.02895 0.01956 -0.0885 0.0308 1.0000
8.500 1.2484 0.03058 0.02126 -0.0865 0.0262 1.0000
8.750 1.2598 0.03210 0.02296 -0.0844 0.0233 1.0000
9.000 1.2675 0.03374 0.02478 -0.0820 0.0217 1.0000
9.250 1.2715 0.03553 0.02673 -0.0792 0.0205 1.0000
9.500 1.2721 0.03764 0.02897 -0.0763 0.0196 1.0000
9.750 1.2705 0.04012 0.03156 -0.0736 0.0187 1.0000
10.000 1.2764 0.04210 0.03373 -0.0717 0.0180 1.0000
10.250 1.2820 0.04423 0.03607 -0.0699 0.0172 1.0000
10.500 1.2872 0.04657 0.03860 -0.0683 0.0164 1.0000
10.750 1.2924 0.04916 0.04149 -0.0667 0.0159 1.0000
11.000 1.2976 0.05194 0.04449 -0.0654 0.0155 1.0000
11.250 1.3017 0.05495 0.04773 -0.0641 0.0152 1.0000
11.500 1.3039 0.05822 0.05126 -0.0631 0.0149 1.0000
11.750 1.3034 0.06181 0.05512 -0.0622 0.0147 1.0000
12.000 1.2999 0.06575 0.05934 -0.0617 0.0145 1.0000
12.250 1.2936 0.07007 0.06393 -0.0617 0.0144 1.0000
12.500 1.2845 0.07480 0.06894 -0.0622 0.0143 1.0000
12.750 1.2730 0.08000 0.07441 -0.0633 0.0142 1.0000
13.000 1.2594 0.08571 0.08038 -0.0652 0.0141 1.0000
13.250 1.2440 0.09202 0.08695 -0.0678 0.0142 1.0000
13.500 1.2270 0.09899 0.09417 -0.0713 0.0142 1.0000
13.750 1.2084 0.10678 0.10219 -0.0757 0.0143 1.0000
14.000 1.1888 0.11550 0.11113 -0.0811 0.0144 1.0000
14.250 1.1682 0.12528 0.12112 -0.0876 0.0147 1.0000
14.500 1.1463 0.13647 0.13248 -0.0953 0.0150 1.0000
14.750 1.1233 0.14928 0.14541 -0.1039 0.0153 1.0000
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Polar data table (+)
Polar graphs
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