FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-140 AIRFOIL (fx61140-il) Reynolds number: 200,000 Max Cl/Cd: 69.25 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61140-il-200000.txt Download as CSV file: xf-fx61140-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4117 0.08910 0.08580 -0.0440 1.0000 0.0481
-9.250 -0.4251 0.08255 0.07931 -0.0486 1.0000 0.0501
-9.000 -0.4381 0.07681 0.07362 -0.0515 1.0000 0.0485
-8.750 -0.4608 0.07149 0.06831 -0.0538 1.0000 0.0477
-8.500 -0.4876 0.06783 0.06464 -0.0536 1.0000 0.0475
-8.250 -0.5177 0.06518 0.06201 -0.0513 1.0000 0.0465
-8.000 -0.5374 0.06221 0.05899 -0.0504 1.0000 0.0474
-7.750 -0.5531 0.05955 0.05624 -0.0487 1.0000 0.0488
-7.500 -0.5653 0.05699 0.05353 -0.0470 1.0000 0.0501
-7.250 -0.5696 0.05343 0.04920 -0.0504 0.9965 0.0539
-7.000 -0.5418 0.04853 0.04465 -0.0529 0.9935 0.0578
-6.750 -0.5085 0.04405 0.03958 -0.0597 0.9863 0.0685
-6.500 -0.4757 0.04056 0.03608 -0.0629 0.9804 0.0731
-6.250 -0.4386 0.03681 0.03197 -0.0679 0.9746 0.0846
-6.000 -0.4033 0.03380 0.02871 -0.0717 0.9672 0.0983
-5.750 -0.3529 0.02489 0.01811 -0.0682 0.9645 0.0286
-5.250 -0.2772 0.02093 0.01373 -0.0714 0.9514 0.0298
-5.000 -0.2387 0.01885 0.01174 -0.0738 0.9470 0.0345
-4.750 -0.2039 0.01752 0.01037 -0.0750 0.9368 0.0377
-4.500 -0.1635 0.01589 0.00874 -0.0779 0.9290 0.0443
-4.250 -0.1181 0.01448 0.00731 -0.0821 0.9211 0.0645
-4.000 -0.0616 0.01118 0.00649 -0.0911 0.9141 0.5855
-3.750 -0.0201 0.01167 0.00688 -0.0925 0.9016 0.6285
-3.500 0.0164 0.01259 0.00772 -0.0923 0.8851 0.6556
-3.250 0.0468 0.01385 0.00893 -0.0900 0.8659 0.6739
-3.000 0.0800 0.01452 0.00943 -0.0895 0.8450 0.6853
-2.750 0.1164 0.01462 0.00928 -0.0911 0.8222 0.6956
-2.500 0.1424 0.01491 0.00942 -0.0898 0.8005 0.6989
-2.250 0.1694 0.01510 0.00942 -0.0891 0.7798 0.7046
-2.000 0.1991 0.01512 0.00922 -0.0896 0.7614 0.7116
-1.750 0.2226 0.01530 0.00926 -0.0882 0.7438 0.7154
-1.500 0.2546 0.01522 0.00899 -0.0898 0.7270 0.7240
-1.250 0.2767 0.01536 0.00902 -0.0881 0.7124 0.7267
-1.000 0.3012 0.01546 0.00901 -0.0871 0.6987 0.7308
-0.750 0.3337 0.01541 0.00878 -0.0888 0.6855 0.7384
-0.500 0.3564 0.01551 0.00878 -0.0874 0.6741 0.7411
-0.250 0.3809 0.01556 0.00877 -0.0866 0.6620 0.7451
0.000 0.4128 0.01554 0.00864 -0.0881 0.6506 0.7517
0.250 0.4369 0.01559 0.00862 -0.0872 0.6407 0.7549
0.500 0.4619 0.01566 0.00862 -0.0865 0.6314 0.7585
0.750 0.4906 0.01568 0.00860 -0.0871 0.6213 0.7638
1.000 0.5195 0.01571 0.00855 -0.0876 0.6125 0.7681
1.250 0.5438 0.01576 0.00858 -0.0868 0.6040 0.7712
1.500 0.5710 0.01582 0.00861 -0.0869 0.5956 0.7754
1.750 0.6054 0.01589 0.00857 -0.0889 0.5876 0.7807
2.000 0.6282 0.01590 0.00863 -0.0878 0.5793 0.7832
2.250 0.6544 0.01601 0.00869 -0.0875 0.5725 0.7866
2.500 0.6821 0.01605 0.00878 -0.0878 0.5639 0.7908
2.750 0.7154 0.01616 0.00882 -0.0895 0.5567 0.7951
3.000 0.7384 0.01619 0.00893 -0.0885 0.5489 0.7978
3.250 0.7648 0.01631 0.00902 -0.0883 0.5424 0.8011
3.500 0.7930 0.01639 0.00917 -0.0887 0.5345 0.8049
3.750 0.8261 0.01656 0.00929 -0.0903 0.5277 0.8091
4.000 0.8492 0.01661 0.00946 -0.0894 0.5202 0.8117
4.250 0.8764 0.01677 0.00959 -0.0894 0.5143 0.8147
4.500 0.9032 0.01688 0.00982 -0.0895 0.5064 0.8184
4.750 0.9356 0.01710 0.01000 -0.0908 0.5000 0.8222
5.000 0.9606 0.01718 0.01025 -0.0905 0.4921 0.8250
5.500 1.0125 0.01747 0.01068 -0.0901 0.4776 0.8312
5.750 1.0430 0.01770 0.01090 -0.0910 0.4710 0.8347
6.000 1.0707 0.01785 0.01124 -0.0914 0.4625 0.8377
6.250 1.0955 0.01798 0.01141 -0.0908 0.4548 0.8404
6.500 1.1196 0.01802 0.01154 -0.0902 0.4448 0.8437
6.750 1.1445 0.01806 0.01169 -0.0899 0.4329 0.8471
7.000 1.1705 0.01804 0.01174 -0.0899 0.4185 0.8503
7.250 1.1921 0.01800 0.01181 -0.0888 0.4039 0.8532
7.500 1.2133 0.01803 0.01194 -0.0877 0.3896 0.8565
7.750 1.2362 0.01814 0.01216 -0.0870 0.3752 0.8598
8.000 1.2600 0.01831 0.01242 -0.0866 0.3593 0.8631
8.250 1.2812 0.01850 0.01270 -0.0857 0.3389 0.8664
8.500 1.2971 0.01877 0.01298 -0.0838 0.3097 0.8697
8.750 1.3104 0.01938 0.01350 -0.0818 0.2648 0.8732
9.000 1.3165 0.02071 0.01445 -0.0791 0.1960 0.8769
9.250 1.3111 0.02274 0.01598 -0.0750 0.1248 0.8806
9.500 1.3034 0.02465 0.01761 -0.0704 0.0824 0.8846
9.750 1.3001 0.02659 0.01940 -0.0669 0.0583 0.8886
10.000 1.2995 0.02856 0.02139 -0.0642 0.0442 0.8925
10.250 1.2910 0.03084 0.02371 -0.0607 0.0351 0.8967
10.500 1.2819 0.03353 0.02650 -0.0581 0.0281 0.9016
10.750 1.2719 0.03683 0.02997 -0.0564 0.0245 0.9063
11.000 1.2668 0.03967 0.03295 -0.0551 0.0222 0.9108
11.250 1.2613 0.04288 0.03628 -0.0544 0.0206 0.9158
11.500 1.2530 0.04672 0.04022 -0.0542 0.0194 0.9207
11.750 1.2421 0.05058 0.04417 -0.0532 0.0184 0.9261
12.000 1.2461 0.05307 0.04682 -0.0530 0.0175 0.9333
12.250 1.2465 0.05564 0.04953 -0.0524 0.0164 0.9425
12.500 1.2458 0.05826 0.05229 -0.0519 0.0155 0.9587
12.750 1.2475 0.06126 0.05540 -0.0523 0.0147 1.0000
13.000 1.2530 0.06445 0.05871 -0.0531 0.0141 1.0000
13.250 1.2590 0.06756 0.06190 -0.0535 0.0136 1.0000
13.500 1.2663 0.07060 0.06502 -0.0534 0.0130 1.0000
13.750 1.2756 0.07379 0.06836 -0.0525 0.0127 1.0000
14.000 1.2802 0.07797 0.07276 -0.0523 0.0125 1.0000
14.250 1.2796 0.08245 0.07748 -0.0538 0.0124 1.0000
14.500 1.2768 0.08735 0.08262 -0.0555 0.0124 1.0000
14.750 1.2703 0.09281 0.08833 -0.0577 0.0124 1.0000
15.000 1.2632 0.09863 0.09437 -0.0600 0.0124 1.0000
15.250 1.2530 0.10499 0.10097 -0.0630 0.0125 1.0000
15.500 1.2428 0.11142 0.10764 -0.0665 0.0125 1.0000
15.750 1.2343 0.11762 0.11404 -0.0704 0.0126 1.0000
16.000 1.2263 0.12395 0.12055 -0.0747 0.0127 1.0000
16.250 1.2135 0.13150 0.12831 -0.0798 0.0127 1.0000
16.500 1.2038 0.13872 0.13571 -0.0851 0.0128 1.0000
16.750 1.1926 0.14666 0.14385 -0.0911 0.0130 1.0000
17.000 1.1749 0.15685 0.15429 -0.0988 0.0133 1.0000
17.250 0.8665 0.17032 0.16851 -0.0926 0.0163 0.9241
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