FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-140 AIRFOIL (fx61140-il) Reynolds number: 100,000 Max Cl/Cd: 52.04 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61140-il-100000-n5.txt Download as CSV file: xf-fx61140-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-140 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2950 0.11615 0.11140 -0.0380 1.0000 0.0276
-11.500 -0.2973 0.11187 0.10715 -0.0391 1.0000 0.0261
-11.000 -0.4090 0.10771 0.10266 -0.0410 1.0000 0.0222
-10.750 -0.4084 0.10405 0.09904 -0.0413 1.0000 0.0217
-10.500 -0.4106 0.09934 0.09438 -0.0429 1.0000 0.0214
-10.250 -0.4134 0.09461 0.08970 -0.0447 1.0000 0.0211
-10.000 -0.4185 0.08911 0.08426 -0.0470 1.0000 0.0208
-9.750 -0.4269 0.08268 0.07788 -0.0505 1.0000 0.0204
-9.500 -0.4403 0.07663 0.07184 -0.0539 1.0000 0.0200
-9.250 -0.4572 0.07144 0.06664 -0.0563 1.0000 0.0196
-9.000 -0.4764 0.06721 0.06239 -0.0573 1.0000 0.0194
-8.750 -0.4996 0.06372 0.05887 -0.0567 1.0000 0.0193
-8.500 -0.5219 0.06122 0.05636 -0.0545 1.0000 0.0190
-8.250 -0.5390 0.05805 0.05311 -0.0535 1.0000 0.0190
-8.000 -0.5514 0.05489 0.04981 -0.0520 1.0000 0.0189
-7.750 -0.5597 0.05170 0.04643 -0.0505 1.0000 0.0188
-7.500 -0.5633 0.04854 0.04303 -0.0490 1.0000 0.0186
-7.250 -0.5505 0.04437 0.03846 -0.0506 0.9968 0.0185
-7.000 -0.5215 0.03972 0.03324 -0.0544 0.9895 0.0185
-6.750 -0.4893 0.03585 0.02882 -0.0575 0.9825 0.0188
-6.500 -0.4561 0.03266 0.02515 -0.0598 0.9750 0.0192
-6.250 -0.4232 0.03005 0.02208 -0.0613 0.9668 0.0201
-6.000 -0.3861 0.02835 0.01997 -0.0632 0.9595 0.0221
-5.750 -0.3569 0.02615 0.01775 -0.0640 0.9496 0.0244
-5.500 -0.3254 0.02460 0.01611 -0.0648 0.9397 0.0261
-5.250 -0.2917 0.02314 0.01457 -0.0659 0.9309 0.0284
-5.000 -0.2590 0.02191 0.01324 -0.0670 0.9202 0.0324
-4.750 -0.2261 0.02064 0.01193 -0.0686 0.9084 0.0386
-4.500 -0.1896 0.01947 0.01066 -0.0708 0.8967 0.0482
-4.250 -0.1503 0.01821 0.00946 -0.0737 0.8854 0.0758
-4.000 -0.1065 0.01520 0.00850 -0.0801 0.8754 0.4550
-3.750 -0.0793 0.01592 0.00960 -0.0778 0.8599 0.5877
-3.500 -0.0492 0.01722 0.01075 -0.0758 0.8437 0.6418
-3.250 -0.0194 0.01795 0.01128 -0.0744 0.8270 0.6596
-3.000 0.0175 0.01797 0.01102 -0.0759 0.8101 0.6701
-2.750 0.0501 0.01808 0.01088 -0.0763 0.7932 0.6764
-2.500 0.0855 0.01803 0.01055 -0.0778 0.7763 0.6844
-2.250 0.1153 0.01810 0.01042 -0.0778 0.7597 0.6894
-2.000 0.1494 0.01800 0.01008 -0.0795 0.7433 0.6974
-1.750 0.1766 0.01808 0.00999 -0.0790 0.7280 0.7011
-1.500 0.2062 0.01809 0.00982 -0.0794 0.7135 0.7066
-1.250 0.2375 0.01804 0.00959 -0.0804 0.6998 0.7125
-1.000 0.2641 0.01810 0.00951 -0.0800 0.6871 0.7163
-0.750 0.2932 0.01812 0.00938 -0.0804 0.6751 0.7215
-0.500 0.3229 0.01811 0.00924 -0.0811 0.6630 0.7268
-0.250 0.3485 0.01817 0.00921 -0.0806 0.6519 0.7303
0.000 0.3768 0.01821 0.00914 -0.0809 0.6417 0.7348
0.250 0.4080 0.01822 0.00903 -0.0820 0.6317 0.7401
0.500 0.4330 0.01828 0.00905 -0.0814 0.6215 0.7432
0.750 0.4601 0.01834 0.00905 -0.0814 0.6125 0.7469
1.000 0.4900 0.01840 0.00902 -0.0822 0.6035 0.7515
1.250 0.5180 0.01846 0.00905 -0.0825 0.5942 0.7553
1.500 0.5442 0.01855 0.00910 -0.0822 0.5864 0.7584
1.750 0.5713 0.01863 0.00917 -0.0823 0.5776 0.7621
2.000 0.6016 0.01873 0.00923 -0.0832 0.5697 0.7666
2.250 0.6285 0.01883 0.00935 -0.0832 0.5619 0.7698
2.500 0.6543 0.01895 0.00948 -0.0830 0.5545 0.7730
2.750 0.6820 0.01907 0.00961 -0.0832 0.5471 0.7766
3.000 0.7118 0.01922 0.00977 -0.0840 0.5396 0.7808
3.250 0.7385 0.01935 0.00995 -0.0840 0.5325 0.7838
3.500 0.7640 0.01950 0.01016 -0.0837 0.5253 0.7869
3.750 0.7912 0.01966 0.01035 -0.0838 0.5182 0.7902
4.000 0.8198 0.01985 0.01061 -0.0844 0.5109 0.7940
4.250 0.8475 0.02003 0.01087 -0.0846 0.5039 0.7972
4.500 0.8726 0.02022 0.01115 -0.0843 0.4969 0.8001
4.750 0.8990 0.02042 0.01143 -0.0842 0.4900 0.8033
5.000 0.9269 0.02066 0.01180 -0.0846 0.4832 0.8069
5.250 0.9557 0.02092 0.01216 -0.0852 0.4760 0.8104
5.500 0.9803 0.02114 0.01250 -0.0847 0.4695 0.8131
5.750 1.0056 0.02138 0.01289 -0.0845 0.4621 0.8162
6.000 1.0323 0.02165 0.01328 -0.0846 0.4551 0.8197
6.250 1.0601 0.02194 0.01375 -0.0850 0.4471 0.8233
6.500 1.0847 0.02222 0.01419 -0.0846 0.4395 0.8262
6.750 1.1093 0.02248 0.01461 -0.0842 0.4319 0.8294
7.000 1.1337 0.02278 0.01510 -0.0838 0.4227 0.8329
7.250 1.1591 0.02301 0.01547 -0.0837 0.4119 0.8363
7.500 1.1821 0.02319 0.01583 -0.0830 0.3991 0.8396
7.750 1.2017 0.02335 0.01617 -0.0817 0.3838 0.8429
8.000 1.2204 0.02353 0.01650 -0.0804 0.3637 0.8467
8.250 1.2390 0.02381 0.01686 -0.0791 0.3395 0.8504
8.500 1.2552 0.02422 0.01734 -0.0775 0.3138 0.8539
8.750 1.2694 0.02476 0.01795 -0.0756 0.2883 0.8576
9.000 1.2817 0.02553 0.01875 -0.0737 0.2539 0.8619
9.250 1.2875 0.02680 0.01983 -0.0712 0.2066 0.8663
9.500 1.2820 0.02841 0.02120 -0.0671 0.1608 0.8704
9.750 1.2736 0.03060 0.02318 -0.0633 0.1197 0.8753
10.000 1.2652 0.03306 0.02546 -0.0603 0.0892 0.8805
10.250 1.2557 0.03551 0.02784 -0.0573 0.0691 0.8858
10.500 1.2482 0.03822 0.03053 -0.0555 0.0541 0.8916
10.750 1.2410 0.04105 0.03341 -0.0540 0.0440 0.8973
11.000 1.2331 0.04422 0.03661 -0.0532 0.0361 0.9036
11.250 1.2269 0.04746 0.03996 -0.0527 0.0302 0.9107
11.500 1.2177 0.05114 0.04375 -0.0526 0.0266 0.9197
11.750 1.2103 0.05468 0.04750 -0.0524 0.0235 0.9323
12.000 1.2001 0.05856 0.05154 -0.0525 0.0214 0.9602
12.250 1.1903 0.06333 0.05644 -0.0540 0.0196 1.0000
12.500 1.1844 0.06804 0.06131 -0.0556 0.0181 1.0000
12.750 1.1803 0.07257 0.06603 -0.0571 0.0167 1.0000
13.000 1.1770 0.07706 0.07068 -0.0587 0.0156 1.0000
13.250 1.1743 0.08154 0.07529 -0.0604 0.0147 1.0000
13.500 1.1719 0.08602 0.07989 -0.0621 0.0140 1.0000
13.750 1.1699 0.09047 0.08446 -0.0637 0.0134 1.0000
14.000 1.1683 0.09478 0.08885 -0.0651 0.0128 1.0000
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