FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il) Reynolds number: 50,000 Max Cl/Cd: 26.92 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx62k153-il-50000.txt Download as CSV file: xf-fx62k153-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX 62-K-153/20 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4400 0.12200 0.11652 -0.0115 1.0001 0.3283
-7.500 -0.4488 0.12033 0.11492 -0.0091 1.0001 0.3446
-7.250 -0.4607 0.11889 0.11356 -0.0065 1.0001 0.3606
-7.000 -0.4423 0.11511 0.10975 -0.0044 1.0001 0.3795
-6.750 -0.4361 0.11262 0.10729 -0.0021 1.0001 0.3988
-6.500 -0.4489 0.11152 0.10626 0.0012 1.0001 0.4199
-6.250 -0.4350 0.10837 0.10312 0.0033 1.0001 0.4414
-6.000 -0.4485 0.10758 0.10241 0.0071 1.0001 0.4656
-5.000 -0.5491 0.06307 0.05664 -0.0522 1.0001 0.1614
-4.750 -0.5061 0.05612 0.04863 -0.0591 1.0001 0.1313
-4.500 -0.4646 0.05163 0.04307 -0.0636 1.0001 0.1189
-4.250 -0.4322 0.04866 0.03956 -0.0658 1.0001 0.1188
-4.000 -0.3997 0.04641 0.03669 -0.0675 1.0001 0.1199
-3.750 -0.3707 0.04417 0.03414 -0.0681 1.0001 0.1206
-3.500 -0.3457 0.04240 0.03232 -0.0680 1.0001 0.1246
-3.250 -0.3202 0.04139 0.03106 -0.0677 1.0001 0.1327
-3.000 -0.2988 0.04038 0.03006 -0.0660 1.0001 0.1393
-2.750 -0.2780 0.03985 0.02943 -0.0641 1.0001 0.1501
-2.500 -0.2576 0.03918 0.02894 -0.0625 1.0001 0.1687
-2.250 -0.2230 0.03819 0.02836 -0.0645 1.0001 0.2157
-1.750 -0.2410 0.04028 0.03320 -0.0406 1.0001 0.7638
-1.500 -0.2590 0.04068 0.03354 -0.0283 1.0001 0.8091
-1.250 -0.2736 0.04055 0.03331 -0.0174 1.0001 0.8521
-1.000 -0.1803 0.04176 0.03379 -0.0201 1.0001 0.9999
-0.750 -0.1777 0.04140 0.03326 -0.0180 1.0001 0.9999
-0.500 -0.1749 0.04104 0.03275 -0.0160 1.0001 0.9999
-0.250 -0.1719 0.04070 0.03227 -0.0140 1.0001 0.9999
0.000 -0.1683 0.04037 0.03182 -0.0121 1.0001 0.9999
0.250 -0.1641 0.04007 0.03140 -0.0103 1.0001 0.9999
0.500 -0.1580 0.03988 0.03107 -0.0089 1.0001 0.9999
0.750 -0.1477 0.03989 0.03095 -0.0083 1.0001 0.9999
1.000 -0.1331 0.04015 0.03107 -0.0086 1.0001 0.9999
1.250 -0.1150 0.04063 0.03141 -0.0095 1.0001 0.9999
1.500 -0.0942 0.04131 0.03195 -0.0109 1.0001 0.9999
1.750 -0.0716 0.04216 0.03267 -0.0127 1.0001 0.9999
2.000 -0.0479 0.04314 0.03353 -0.0148 1.0001 0.9999
2.250 -0.0234 0.04424 0.03453 -0.0170 1.0001 0.9999
2.500 0.0015 0.04544 0.03563 -0.0193 1.0001 0.9999
2.750 0.0266 0.04673 0.03684 -0.0217 1.0001 0.9999
3.000 0.0517 0.04810 0.03816 -0.0242 1.0001 0.9999
3.250 0.0766 0.04956 0.03955 -0.0267 1.0001 0.9999
3.500 0.1027 0.05116 0.04111 -0.0294 0.9993 0.9999
3.750 0.1428 0.05378 0.04368 -0.0349 0.9932 0.9999
4.000 0.1884 0.05697 0.04682 -0.0414 0.9855 0.9999
4.250 0.2229 0.05922 0.04907 -0.0457 0.9747 0.9999
4.500 0.2552 0.06136 0.05122 -0.0496 0.9628 0.9999
4.750 0.2854 0.06343 0.05331 -0.0531 0.9502 0.9999
5.000 0.3143 0.06549 0.05541 -0.0562 0.9374 0.9999
5.250 0.3428 0.06762 0.05758 -0.0593 0.9241 0.9999
5.500 0.3709 0.06981 0.05983 -0.0623 0.9108 0.9999
5.750 0.3987 0.07203 0.06212 -0.0652 0.8970 0.9999
6.000 0.4260 0.07428 0.06445 -0.0680 0.8826 0.9999
6.250 0.4528 0.07654 0.06679 -0.0707 0.8675 0.9999
6.500 0.4801 0.07885 0.06922 -0.0734 0.8515 0.9999
6.750 0.5101 0.08133 0.07180 -0.0764 0.8346 0.9999
7.000 0.5523 0.08461 0.07520 -0.0810 0.8164 0.9999
7.250 0.6053 0.08407 0.07478 -0.0828 0.7562 0.9999
7.500 0.6598 0.08347 0.07431 -0.0849 0.7128 0.9999
7.750 0.6773 0.08472 0.07572 -0.0852 0.6924 0.9999
8.000 0.7175 0.08577 0.07694 -0.0876 0.6730 0.9999
8.250 0.7453 0.08700 0.07835 -0.0887 0.6543 0.9999
8.500 0.7662 0.08827 0.07981 -0.0893 0.6347 0.9999
8.750 0.8184 0.08802 0.07980 -0.0915 0.6144 0.9999
9.000 0.8349 0.08925 0.08119 -0.0913 0.5938 0.9999
9.250 0.8685 0.08939 0.08159 -0.0918 0.5738 0.9999
9.500 0.9211 0.08744 0.07994 -0.0923 0.5536 0.9999
9.750 0.9381 0.08804 0.08075 -0.0915 0.5308 0.9999
10.000 1.0248 0.08062 0.07384 -0.0908 0.5106 0.9999
10.250 1.0455 0.07981 0.07329 -0.0888 0.4853 0.9999
10.500 1.2404 0.05250 0.04690 -0.0837 0.4471 0.9999
10.750 1.2840 0.04770 0.04168 -0.0795 0.3701 0.9999
11.000 1.2879 0.04899 0.04240 -0.0758 0.3113 0.9999
11.250 1.2952 0.05102 0.04388 -0.0731 0.2633 0.9999
11.500 1.3068 0.05327 0.04578 -0.0713 0.2263 0.9999
11.750 1.3246 0.05553 0.04784 -0.0701 0.1966 0.9999
12.000 1.3553 0.05773 0.04983 -0.0698 0.1709 0.9999
12.250 1.3777 0.06053 0.05273 -0.0693 0.1535 0.9999
12.500 1.4049 0.06384 0.05619 -0.0691 0.1394 0.9999
12.750 1.4232 0.06740 0.05994 -0.0686 0.1284 0.9999
13.000 1.4315 0.07130 0.06418 -0.0672 0.1216 0.9999
13.250 1.4329 0.07555 0.06865 -0.0657 0.1156 0.9999
13.500 1.4125 0.07972 0.07324 -0.0630 0.1136 0.9999
13.750 1.3927 0.08422 0.07811 -0.0610 0.1117 0.9999
14.000 1.3725 0.08908 0.08329 -0.0594 0.1102 0.9999
14.250 1.3460 0.09455 0.08908 -0.0584 0.1102 0.9999
14.500 1.3130 0.10082 0.09568 -0.0584 0.1115 0.9999
14.750 1.2798 0.10780 0.10292 -0.0595 0.1132 0.9999
15.000 1.2482 0.11548 0.11080 -0.0618 0.1148 0.9999
15.250 1.2198 0.12373 0.11915 -0.0650 0.1163 0.9999
15.500 1.1954 0.13249 0.12801 -0.0690 0.1174 0.9999
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