FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: FX 61-147 AIRFOIL (fx61147-il) Reynolds number: 50,000 Max Cl/Cd: 8.36 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61147-il-50000.txt Download as CSV file: xf-fx61147-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3024 0.11030 0.10386 -0.0255 1.0000 0.3324
-8.750 -0.3063 0.10820 0.10186 -0.0243 1.0000 0.3454
-8.500 -0.3120 0.10635 0.10013 -0.0228 1.0000 0.3592
-8.250 -0.2963 0.10259 0.09638 -0.0217 1.0000 0.3697
-8.000 -0.2947 0.09975 0.09363 -0.0204 1.0000 0.3785
-7.750 -0.3024 0.09785 0.09186 -0.0185 1.0000 0.3906
-7.500 -0.2969 0.09478 0.08885 -0.0173 1.0000 0.3961
-7.250 -0.3107 0.09311 0.08734 -0.0149 1.0000 0.4055
-7.000 -0.3980 0.08675 0.08134 -0.0211 1.0000 0.2875
-6.750 -0.4481 0.08544 0.08033 -0.0181 1.0000 0.2846
-6.500 -0.5458 0.06940 0.06411 -0.0376 1.0000 0.1810
-6.250 -0.5516 0.06196 0.05613 -0.0420 1.0000 0.1462
-6.000 -0.5457 0.05676 0.05041 -0.0440 1.0000 0.1313
-5.750 -0.5309 0.05221 0.04487 -0.0467 1.0000 0.1197
-5.500 -0.5149 0.04885 0.04135 -0.0468 1.0000 0.1180
-5.250 -0.4961 0.04569 0.03787 -0.0473 1.0000 0.1154
-5.000 -0.4742 0.04277 0.03448 -0.0479 1.0000 0.1121
-4.750 -0.4516 0.04038 0.03161 -0.0481 1.0000 0.1103
-4.500 -0.4313 0.03868 0.02963 -0.0479 1.0000 0.1129
-4.250 -0.4106 0.03730 0.02789 -0.0475 1.0000 0.1169
-4.000 -0.3902 0.03618 0.02640 -0.0468 1.0000 0.1197
-3.750 -0.3712 0.03491 0.02523 -0.0455 0.9991 0.1240
-3.500 -0.3280 0.03417 0.02452 -0.0475 0.9886 0.1387
-3.250 -0.2892 0.03344 0.02390 -0.0489 0.9777 0.1582
-3.000 -0.2467 0.03169 0.02271 -0.0526 0.9669 0.2211
-2.750 -0.2516 0.03330 0.02700 -0.0400 0.9546 0.6815
-2.500 -0.2571 0.03585 0.02940 -0.0282 0.9414 0.7465
-2.250 -0.2614 0.03707 0.03050 -0.0179 0.9290 0.7932
-2.000 -0.1044 0.03932 0.03181 -0.0246 0.9255 0.9415
-1.750 -0.0313 0.03894 0.03097 -0.0348 0.9141 0.9578
-1.500 0.0436 0.03851 0.03013 -0.0455 0.9030 0.9710
-1.250 0.1207 0.03799 0.02926 -0.0565 0.8925 0.9825
-1.000 0.1778 0.03763 0.02865 -0.0641 0.8798 0.9919
-0.750 0.2308 0.03741 0.02824 -0.0709 0.8679 1.0000
-0.500 0.2508 0.03756 0.02827 -0.0715 0.8555 1.0000
-0.250 0.2765 0.03764 0.02824 -0.0728 0.8446 1.0000
0.000 0.3008 0.03775 0.02825 -0.0738 0.8337 1.0000
0.250 0.3019 0.03836 0.02882 -0.0712 0.8212 1.0000
0.500 0.3038 0.03900 0.02940 -0.0688 0.8098 1.0000
0.750 0.3224 0.03933 0.02966 -0.0687 0.8002 1.0000
1.000 0.3328 0.03981 0.03008 -0.0674 0.7899 1.0000
1.250 0.3160 0.04085 0.03112 -0.0624 0.7791 1.0000
1.500 0.3269 0.04139 0.03160 -0.0611 0.7703 1.0000
1.750 0.3240 0.04213 0.03232 -0.0579 0.7608 1.0000
2.000 0.3055 0.04316 0.03334 -0.0529 0.7518 1.0000
2.250 0.3256 0.04357 0.03370 -0.0527 0.7442 1.0000
2.500 0.2941 0.04478 0.03491 -0.0464 0.7355 1.0000
2.750 0.3275 0.04522 0.03529 -0.0479 0.7284 1.0000
3.000 0.3101 0.04680 0.03687 -0.0447 0.7198 1.0000
3.250 0.3437 0.04764 0.03766 -0.0468 0.7121 1.0000
3.500 0.3464 0.04935 0.03937 -0.0465 0.7042 1.0000
3.750 0.3775 0.05050 0.04050 -0.0486 0.6963 1.0000
4.000 0.3881 0.05229 0.04230 -0.0493 0.6885 1.0000
4.250 0.4161 0.05373 0.04374 -0.0513 0.6809 1.0000
4.500 0.4293 0.05565 0.04568 -0.0524 0.6732 1.0000
4.750 0.4553 0.05731 0.04736 -0.0543 0.6657 1.0000
5.000 0.4657 0.05952 0.04961 -0.0554 0.6590 1.0000
5.250 0.4951 0.06120 0.05131 -0.0575 0.6514 1.0000
5.500 0.4981 0.06389 0.05405 -0.0583 0.6462 1.0000
5.750 0.5364 0.06536 0.05558 -0.0607 0.6376 1.0000
6.000 0.5335 0.06853 0.05880 -0.0615 0.6348 1.0000
6.250 0.5388 0.07149 0.06182 -0.0628 0.6325 1.0000
6.500 0.5458 0.07459 0.06498 -0.0643 0.6325 1.0000
6.750 0.5580 0.07797 0.06844 -0.0665 0.6362 1.0000
7.000 0.4755 0.08583 0.07642 -0.0684 0.7404 1.0000
7.250 0.5078 0.08903 0.07969 -0.0715 0.7287 1.0000
7.500 0.5160 0.09078 0.08149 -0.0717 0.7162 1.0000
7.750 0.5292 0.09311 0.08388 -0.0727 0.7043 1.0000
8.000 0.5482 0.09597 0.08684 -0.0743 0.6943 1.0000
8.250 0.5818 0.09966 0.09062 -0.0773 0.6831 1.0000
8.500 0.5965 0.10198 0.09303 -0.0782 0.6694 1.0000
8.750 0.6048 0.10415 0.09528 -0.0786 0.6564 1.0000
9.000 0.6161 0.10672 0.09796 -0.0794 0.6437 1.0000
9.250 0.6299 0.10960 0.10092 -0.0805 0.6319 1.0000
9.500 0.6489 0.11282 0.10425 -0.0821 0.6202 1.0000
9.750 0.6767 0.11661 0.10816 -0.0842 0.6078 1.0000
10.000 0.6969 0.11984 0.11155 -0.0855 0.5937 1.0000
10.250 0.7030 0.12222 0.11403 -0.0859 0.5797 1.0000
10.500 0.7076 0.12482 0.11671 -0.0864 0.5666 1.0000
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Polar data table (+)
Polar graphs
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