FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-147 AIRFOIL (fx61147-il) Reynolds number: 100,000 Max Cl/Cd: 52.25 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61147-il-100000-n5.txt Download as CSV file: xf-fx61147-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3699 0.09963 0.09475 -0.0501 1.0000 0.0223
-10.250 -0.3730 0.09559 0.09077 -0.0509 1.0000 0.0221
-10.000 -0.3781 0.09110 0.08634 -0.0521 1.0000 0.0219
-9.750 -0.3862 0.08587 0.08118 -0.0540 1.0000 0.0216
-9.500 -0.3971 0.08058 0.07595 -0.0561 1.0000 0.0213
-9.250 -0.4148 0.07543 0.07083 -0.0579 1.0000 0.0210
-9.000 -0.4383 0.07104 0.06647 -0.0586 1.0000 0.0208
-8.750 -0.4625 0.06804 0.06349 -0.0574 1.0000 0.0205
-8.500 -0.4925 0.06587 0.06134 -0.0545 1.0000 0.0205
-8.250 -0.5051 0.06148 0.05682 -0.0576 0.9949 0.0203
-8.000 -0.4973 0.05509 0.05004 -0.0642 0.9839 0.0201
-7.750 -0.4836 0.04957 0.04408 -0.0689 0.9744 0.0200
-7.500 -0.4673 0.04469 0.03871 -0.0718 0.9643 0.0202
-7.250 -0.4469 0.04055 0.03406 -0.0739 0.9549 0.0204
-7.000 -0.4174 0.03646 0.02937 -0.0766 0.9489 0.0210
-6.750 -0.3914 0.03358 0.02582 -0.0774 0.9394 0.0226
-6.500 -0.3599 0.03138 0.02351 -0.0796 0.9334 0.0245
-6.000 -0.2964 0.02755 0.01914 -0.0817 0.9189 0.0284
-5.750 -0.2665 0.02596 0.01738 -0.0821 0.9103 0.0315
-5.500 -0.2342 0.02453 0.01593 -0.0831 0.9032 0.0343
-5.250 -0.2024 0.02332 0.01460 -0.0838 0.8947 0.0378
-5.000 -0.1720 0.02216 0.01340 -0.0844 0.8852 0.0422
-4.750 -0.1358 0.02101 0.01221 -0.0864 0.8776 0.0472
-4.500 -0.1043 0.02006 0.01118 -0.0875 0.8662 0.0553
-4.250 -0.0690 0.01910 0.01016 -0.0894 0.8557 0.0696
-4.000 -0.0298 0.01767 0.00910 -0.0926 0.8466 0.1401
-3.750 0.0011 0.01575 0.00898 -0.0949 0.8346 0.5027
-3.500 0.0289 0.01629 0.00963 -0.0933 0.8214 0.5894
-3.250 0.0592 0.01718 0.01036 -0.0921 0.8080 0.6416
-3.000 0.0829 0.01812 0.01121 -0.0890 0.7943 0.6652
-2.750 0.1145 0.01828 0.01114 -0.0892 0.7807 0.6763
-2.500 0.1497 0.01820 0.01079 -0.0907 0.7670 0.6860
-2.250 0.1790 0.01826 0.01066 -0.0905 0.7532 0.6908
-2.000 0.2106 0.01823 0.01043 -0.0912 0.7396 0.6975
-1.750 0.2424 0.01819 0.01017 -0.0921 0.7261 0.7037
-1.500 0.2711 0.01821 0.01002 -0.0921 0.7133 0.7085
-1.250 0.3029 0.01816 0.00978 -0.0932 0.7005 0.7156
-1.000 0.3293 0.01819 0.00969 -0.0928 0.6882 0.7196
-0.750 0.3567 0.01823 0.00959 -0.0927 0.6767 0.7243
-0.500 0.3886 0.01821 0.00941 -0.0940 0.6659 0.7305
-0.250 0.4150 0.01826 0.00934 -0.0936 0.6556 0.7341
0.000 0.4413 0.01830 0.00931 -0.0934 0.6452 0.7382
0.250 0.4711 0.01835 0.00923 -0.0941 0.6359 0.7434
0.500 0.4993 0.01839 0.00918 -0.0944 0.6265 0.7476
0.750 0.5246 0.01847 0.00920 -0.0939 0.6171 0.7512
1.000 0.5533 0.01854 0.00917 -0.0943 0.6091 0.7555
1.250 0.5827 0.01862 0.00920 -0.0951 0.5995 0.7605
1.500 0.6079 0.01871 0.00924 -0.0946 0.5916 0.7636
1.750 0.6338 0.01880 0.00931 -0.0944 0.5832 0.7673
2.000 0.6621 0.01892 0.00939 -0.0947 0.5755 0.7714
2.250 0.6910 0.01904 0.00947 -0.0953 0.5675 0.7756
2.500 0.7160 0.01915 0.00959 -0.0949 0.5603 0.7786
2.750 0.7422 0.01928 0.00974 -0.0948 0.5529 0.7821
3.000 0.7700 0.01944 0.00988 -0.0951 0.5461 0.7861
3.250 0.7981 0.01960 0.01006 -0.0956 0.5386 0.7900
3.750 0.8483 0.01991 0.01045 -0.0949 0.5247 0.7964
4.000 0.8763 0.02010 0.01062 -0.0952 0.5184 0.8002
4.250 0.9037 0.02032 0.01092 -0.0956 0.5105 0.8040
4.750 0.9528 0.02070 0.01145 -0.0947 0.4969 0.8103
5.000 0.9803 0.02091 0.01168 -0.0950 0.4908 0.8140
5.250 1.0068 0.02119 0.01209 -0.0952 0.4835 0.8177
5.500 1.0319 0.02141 0.01237 -0.0949 0.4771 0.8208
5.750 1.0558 0.02167 0.01275 -0.0944 0.4705 0.8243
6.000 1.0811 0.02194 0.01312 -0.0943 0.4637 0.8279
6.250 1.1082 0.02225 0.01353 -0.0945 0.4575 0.8317
6.500 1.1313 0.02256 0.01399 -0.0940 0.4504 0.8350
6.750 1.1567 0.02282 0.01431 -0.0938 0.4447 0.8385
7.000 1.1787 0.02319 0.01488 -0.0931 0.4369 0.8423
7.250 1.2059 0.02349 0.01528 -0.0933 0.4308 0.8461
7.500 1.2255 0.02385 0.01585 -0.0922 0.4223 0.8498
7.750 1.2483 0.02409 0.01616 -0.0915 0.4146 0.8537
8.000 1.2677 0.02444 0.01671 -0.0904 0.4048 0.8580
8.250 1.2880 0.02477 0.01722 -0.0894 0.3951 0.8621
8.500 1.3063 0.02500 0.01754 -0.0879 0.3852 0.8663
8.750 1.3215 0.02533 0.01805 -0.0860 0.3735 0.8715
9.000 1.3366 0.02571 0.01861 -0.0843 0.3616 0.8767
9.250 1.3488 0.02607 0.01912 -0.0819 0.3495 0.8821
9.500 1.3584 0.02648 0.01965 -0.0792 0.3358 0.8883
9.750 1.3639 0.02695 0.02024 -0.0758 0.3207 0.8958
10.000 1.3679 0.02756 0.02099 -0.0725 0.3044 0.9054
10.500 1.3670 0.02907 0.02268 -0.0650 0.2715 0.9697
10.750 1.3724 0.03042 0.02410 -0.0633 0.2510 1.0000
11.000 1.3742 0.03211 0.02580 -0.0615 0.2299 1.0000
11.250 1.3729 0.03417 0.02786 -0.0598 0.2072 1.0000
11.500 1.3675 0.03672 0.03038 -0.0582 0.1841 1.0000
11.750 1.3591 0.03977 0.03338 -0.0570 0.1615 1.0000
12.000 1.3478 0.04336 0.03691 -0.0561 0.1430 1.0000
12.250 1.3362 0.04730 0.04083 -0.0558 0.1261 1.0000
12.500 1.3242 0.05156 0.04509 -0.0559 0.1114 1.0000
12.750 1.3117 0.05613 0.04967 -0.0564 0.0987 1.0000
13.000 1.2994 0.06090 0.05445 -0.0572 0.0883 1.0000
13.250 1.2868 0.06591 0.05948 -0.0582 0.0793 1.0000
13.500 1.2774 0.07070 0.06434 -0.0594 0.0705 1.0000
13.750 1.2673 0.07572 0.06941 -0.0608 0.0640 1.0000
14.000 1.2575 0.08086 0.07460 -0.0624 0.0580 1.0000
14.250 1.2491 0.08591 0.07976 -0.0640 0.0523 1.0000
14.500 1.2412 0.09103 0.08494 -0.0658 0.0469 1.0000
14.750 1.2341 0.09614 0.09012 -0.0677 0.0422 1.0000
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