FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: FX 61-147 AIRFOIL (fx61147-il) Reynolds number: 100,000 Max Cl/Cd: 50.02 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61147-il-100000.txt Download as CSV file: xf-fx61147-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-147 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3464 0.10624 0.10158 -0.0418 1.0000 0.1123
-9.500 -0.3552 0.10315 0.09858 -0.0429 1.0000 0.1172
-9.250 -0.4012 0.09926 0.09490 -0.0483 1.0000 0.1197
-9.000 -0.3623 0.09663 0.09222 -0.0421 1.0000 0.1252
-8.750 -0.3700 0.09388 0.08957 -0.0419 1.0000 0.1306
-8.500 -0.4144 0.09032 0.08620 -0.0446 1.0000 0.1337
-8.250 -0.4051 0.08741 0.08335 -0.0414 1.0000 0.1379
-8.000 -0.4057 0.08569 0.08169 -0.0387 1.0000 0.1442
-7.750 -0.4375 0.08301 0.07916 -0.0376 1.0000 0.1459
-7.500 -0.4757 0.08072 0.07700 -0.0356 1.0000 0.1462
-7.250 -0.5130 0.07769 0.07405 -0.0360 1.0000 0.1468
-7.000 -0.5627 0.07480 0.07102 -0.0382 1.0000 0.1487
-6.750 -0.5445 0.07238 0.06885 -0.0334 1.0000 0.1545
-6.500 -0.5181 0.06752 0.06390 -0.0404 0.9913 0.1730
-6.250 -0.4917 0.06387 0.06024 -0.0446 0.9820 0.2012
-6.000 -0.4524 0.04708 0.04125 -0.0647 0.9687 0.1044
-5.750 -0.4246 0.04552 0.04035 -0.0681 0.9614 0.1551
-5.500 -0.3645 0.03536 0.02774 -0.0703 0.9557 0.0618
-5.250 -0.3184 0.03217 0.02410 -0.0737 0.9502 0.0613
-5.000 -0.2807 0.02988 0.02145 -0.0755 0.9406 0.0649
-4.750 -0.2349 0.02771 0.01924 -0.0784 0.9355 0.0692
-4.500 -0.1995 0.02643 0.01784 -0.0794 0.9246 0.0756
-4.250 -0.1636 0.02480 0.01638 -0.0806 0.9158 0.0841
-4.000 -0.1211 0.02330 0.01499 -0.0831 0.9085 0.1009
-3.750 -0.0816 0.02126 0.01342 -0.0861 0.8988 0.1634
-3.500 -0.0540 0.02142 0.01579 -0.0823 0.8921 0.6463
-3.250 -0.0354 0.02288 0.01714 -0.0769 0.8793 0.6785
-3.000 -0.0187 0.02412 0.01829 -0.0709 0.8675 0.7058
-2.750 -0.0022 0.02534 0.01946 -0.0636 0.8585 0.7370
-2.500 0.0235 0.02580 0.01979 -0.0594 0.8500 0.7640
-2.250 0.0547 0.02550 0.01930 -0.0591 0.8393 0.7780
-2.000 0.1041 0.02487 0.01843 -0.0628 0.8334 0.7898
-1.750 0.1333 0.02447 0.01788 -0.0625 0.8212 0.7987
-1.500 0.1662 0.02400 0.01725 -0.0634 0.8101 0.8075
-1.250 0.2092 0.02350 0.01654 -0.0664 0.8013 0.8166
-1.000 0.2410 0.02308 0.01598 -0.0668 0.7899 0.8234
-0.750 0.2673 0.02283 0.01559 -0.0672 0.7774 0.8320
-0.500 0.2959 0.02249 0.01514 -0.0671 0.7662 0.8379
-0.250 0.3297 0.02222 0.01471 -0.0686 0.7563 0.8453
0.000 0.3567 0.02196 0.01434 -0.0685 0.7452 0.8511
0.250 0.3786 0.02184 0.01415 -0.0678 0.7338 0.8580
0.500 0.4054 0.02166 0.01387 -0.0680 0.7238 0.8638
0.750 0.4366 0.02147 0.01356 -0.0687 0.7144 0.8694
1.000 0.4554 0.02147 0.01353 -0.0678 0.7036 0.8756
1.250 0.4816 0.02134 0.01333 -0.0676 0.6944 0.8807
1.500 0.5092 0.02127 0.01318 -0.0679 0.6853 0.8864
1.750 0.5286 0.02130 0.01320 -0.0669 0.6756 0.8918
2.000 0.5618 0.02120 0.01299 -0.0680 0.6681 0.8967
2.250 0.5785 0.02133 0.01315 -0.0667 0.6582 0.9026
2.500 0.6048 0.02133 0.01313 -0.0667 0.6503 0.9074
2.750 0.6291 0.02139 0.01317 -0.0664 0.6418 0.9127
3.000 0.6515 0.02157 0.01335 -0.0661 0.6336 0.9180
3.250 0.6798 0.02157 0.01335 -0.0664 0.6258 0.9227
3.500 0.6998 0.02179 0.01361 -0.0655 0.6175 0.9283
3.750 0.7298 0.02188 0.01367 -0.0663 0.6102 0.9331
4.000 0.7494 0.02213 0.01400 -0.0654 0.6017 0.9387
4.250 0.7824 0.02221 0.01406 -0.0666 0.5946 0.9438
4.500 0.8006 0.02257 0.01454 -0.0657 0.5860 0.9495
4.750 0.8373 0.02266 0.01459 -0.0676 0.5793 0.9546
5.000 0.8553 0.02312 0.01521 -0.0667 0.5705 0.9613
5.250 0.8969 0.02324 0.01530 -0.0695 0.5639 0.9659
5.500 0.9171 0.02382 0.01606 -0.0692 0.5548 0.9734
5.750 0.9623 0.02399 0.01623 -0.0727 0.5483 0.9782
6.000 0.9867 0.02465 0.01710 -0.0733 0.5388 0.9868
6.250 1.0259 0.02500 0.01750 -0.0760 0.5318 0.9958
6.500 1.0388 0.02566 0.01832 -0.0744 0.5237 1.0000
6.750 1.0703 0.02602 0.01873 -0.0756 0.5170 1.0000
7.000 1.0890 0.02679 0.01968 -0.0752 0.5084 1.0000
7.250 1.1207 0.02725 0.02022 -0.0765 0.5012 1.0000
7.500 1.1465 0.02783 0.02094 -0.0770 0.4922 1.0000
7.750 1.1726 0.02843 0.02170 -0.0775 0.4831 1.0000
8.000 1.2124 0.02839 0.02168 -0.0797 0.4745 1.0000
8.250 1.2314 0.02918 0.02270 -0.0792 0.4640 1.0000
8.500 1.2615 0.02945 0.02308 -0.0801 0.4539 1.0000
8.750 1.3008 0.02914 0.02279 -0.0819 0.4433 1.0000
9.000 1.3259 0.02927 0.02307 -0.0819 0.4308 1.0000
9.250 1.3493 0.02941 0.02337 -0.0816 0.4179 1.0000
9.500 1.3744 0.02924 0.02330 -0.0813 0.4036 1.0000
9.750 1.3980 0.02887 0.02301 -0.0807 0.3876 1.0000
10.000 1.4188 0.02862 0.02281 -0.0797 0.3712 1.0000
10.250 1.4345 0.02868 0.02297 -0.0781 0.3552 1.0000
10.500 1.4418 0.02905 0.02351 -0.0754 0.3391 1.0000
10.750 1.4441 0.02959 0.02421 -0.0720 0.3221 1.0000
11.000 1.4442 0.03035 0.02510 -0.0686 0.3034 1.0000
11.250 1.4419 0.03135 0.02610 -0.0652 0.2827 1.0000
11.500 1.4327 0.03305 0.02789 -0.0618 0.2580 1.0000
11.750 1.4192 0.03540 0.03019 -0.0587 0.2304 1.0000
12.000 1.4010 0.03861 0.03328 -0.0561 0.2015 1.0000
12.250 1.3804 0.04261 0.03711 -0.0543 0.1751 1.0000
12.500 1.3591 0.04717 0.04147 -0.0533 0.1547 1.0000
12.750 1.3403 0.05193 0.04611 -0.0528 0.1368 1.0000
13.000 1.3247 0.05661 0.05067 -0.0526 0.1219 1.0000
13.250 1.3134 0.06099 0.05499 -0.0526 0.1091 1.0000
13.500 1.3057 0.06509 0.05901 -0.0527 0.0979 1.0000
13.750 1.2993 0.06911 0.06294 -0.0530 0.0880 1.0000
14.000 1.2923 0.07344 0.06730 -0.0540 0.0794 1.0000
14.250 1.2860 0.07786 0.07179 -0.0550 0.0712 1.0000
14.500 1.2814 0.08195 0.07583 -0.0559 0.0636 1.0000
14.750 1.2772 0.08627 0.08022 -0.0570 0.0569 1.0000
15.000 1.2772 0.08996 0.08395 -0.0572 0.0497 1.0000
15.250 1.2864 0.09226 0.08609 -0.0561 0.0426 1.0000
15.500 1.2874 0.09626 0.09037 -0.0568 0.0393 1.0000
15.750 1.2897 0.09988 0.09409 -0.0576 0.0365 1.0000
16.000 1.3017 0.10238 0.09653 -0.0568 0.0334 1.0000
16.250 1.2947 0.10754 0.10200 -0.0589 0.0324 1.0000
16.500 1.2881 0.11283 0.10757 -0.0612 0.0316 1.0000
16.750 1.2802 0.11843 0.11343 -0.0638 0.0309 1.0000
17.000 1.2701 0.12453 0.11979 -0.0670 0.0304 1.0000
17.250 1.2577 0.13124 0.12674 -0.0707 0.0302 1.0000
17.500 1.2424 0.13869 0.13445 -0.0753 0.0303 1.0000
17.750 1.2241 0.14709 0.14309 -0.0808 0.0305 1.0000
18.000 1.2035 0.15645 0.15268 -0.0872 0.0311 1.0000
18.250 1.1809 0.16690 0.16331 -0.0946 0.0318 1.0000
18.500 1.1594 0.17779 0.17433 -0.1022 0.0327 1.0000
18.750 1.1418 0.18833 0.18493 -0.1092 0.0335 1.0000
19.000 1.0668 0.23048 0.22688 -0.1331 0.0506 1.0000
19.250 1.0777 0.23515 0.23158 -0.1345 0.0552 1.0000
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