FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il) Reynolds number: 50,000 Max Cl/Cd: 23 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx62k153-il-50000-n5.txt Download as CSV file: xf-fx62k153-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3725 0.15084 0.14436 -0.0428 0.9985 0.1012
-11.500 -0.3810 0.14809 0.14168 -0.0486 0.9948 0.1047
-11.250 -0.3854 0.14470 0.13834 -0.0529 0.9909 0.1052
-11.000 -0.3598 0.13921 0.13278 -0.0516 0.9891 0.1075
-10.750 -0.3564 0.13018 0.12369 -0.0582 0.9858 0.0612
-10.500 -0.3444 0.12626 0.11972 -0.0584 0.9828 0.0571
-10.250 -0.3627 0.11807 0.11164 -0.0672 0.9775 0.0494
-10.000 -0.3494 0.11466 0.10821 -0.0672 0.9752 0.0484
-9.750 -0.3452 0.11076 0.10429 -0.0687 0.9719 0.0475
-9.500 -0.3453 0.10670 0.10026 -0.0704 0.9678 0.0467
-9.250 -0.3453 0.10200 0.09558 -0.0733 0.9640 0.0459
-9.000 -0.3470 0.09665 0.09025 -0.0772 0.9605 0.0452
-8.750 -0.3587 0.09209 0.08573 -0.0791 0.9549 0.0445
-8.500 -0.3715 0.08716 0.08083 -0.0821 0.9500 0.0437
-8.250 -0.3917 0.08329 0.07695 -0.0832 0.9441 0.0431
-8.000 -0.4103 0.07924 0.07282 -0.0847 0.9377 0.0424
-7.750 -0.4178 0.07423 0.06762 -0.0884 0.9330 0.0420
-7.500 -0.4310 0.07099 0.06421 -0.0875 0.9265 0.0419
-7.250 -0.4297 0.06702 0.05996 -0.0891 0.9221 0.0423
-7.000 -0.4185 0.06291 0.05548 -0.0918 0.9189 0.0436
-6.750 -0.4164 0.05995 0.05216 -0.0912 0.9138 0.0445
-6.500 -0.4018 0.05638 0.04812 -0.0925 0.9100 0.0456
-6.250 -0.3784 0.05271 0.04389 -0.0946 0.9072 0.0463
-6.000 -0.3488 0.04935 0.03990 -0.0969 0.9050 0.0474
-5.750 -0.3265 0.04709 0.03706 -0.0972 0.9016 0.0497
-5.500 -0.3058 0.04524 0.03513 -0.0973 0.8982 0.0528
-5.250 -0.2793 0.04358 0.03319 -0.0976 0.8954 0.0555
-5.000 -0.2509 0.04210 0.03137 -0.0975 0.8929 0.0583
-4.750 -0.2219 0.04100 0.03000 -0.0972 0.8908 0.0635
-4.500 -0.2038 0.04028 0.02930 -0.0955 0.8873 0.0684
-4.250 -0.1863 0.03972 0.02859 -0.0932 0.8833 0.0730
-4.000 -0.1631 0.03904 0.02788 -0.0925 0.8801 0.0813
-3.750 -0.1340 0.03828 0.02703 -0.0932 0.8773 0.0937
-3.500 -0.1004 0.03732 0.02609 -0.0955 0.8749 0.1191
-3.250 -0.0711 0.03564 0.02513 -0.0988 0.8711 0.1990
-2.750 -0.0518 0.03718 0.02854 -0.0879 0.8626 0.6667
-2.500 -0.0482 0.03851 0.02976 -0.0811 0.8578 0.7099
-2.250 -0.0500 0.03955 0.03072 -0.0733 0.8521 0.7495
-2.000 -0.0480 0.04009 0.03116 -0.0657 0.8480 0.7815
-1.750 -0.0376 0.04026 0.03116 -0.0618 0.8435 0.8003
-1.500 -0.0174 0.04035 0.03100 -0.0616 0.8381 0.8088
-1.250 0.0083 0.04036 0.03076 -0.0617 0.8342 0.8153
-1.000 0.0444 0.04047 0.03058 -0.0643 0.8313 0.8221
-0.750 0.0549 0.04061 0.03060 -0.0622 0.8244 0.8276
-0.500 0.0841 0.04076 0.03056 -0.0635 0.8201 0.8333
-0.250 0.1187 0.04089 0.03047 -0.0656 0.8168 0.8384
0.000 0.1320 0.04117 0.03066 -0.0642 0.8098 0.8436
0.250 0.1622 0.04141 0.03074 -0.0658 0.8052 0.8486
0.500 0.1972 0.04157 0.03075 -0.0678 0.8019 0.8529
0.750 0.2098 0.04197 0.03110 -0.0665 0.7942 0.8576
1.000 0.2410 0.04223 0.03125 -0.0681 0.7896 0.8620
1.250 0.2710 0.04257 0.03150 -0.0696 0.7850 0.8661
1.500 0.2882 0.04295 0.03185 -0.0689 0.7776 0.8704
1.750 0.3212 0.04319 0.03201 -0.0705 0.7735 0.8745
2.000 0.3410 0.04377 0.03256 -0.0707 0.7660 0.8789
2.250 0.3684 0.04404 0.03281 -0.0714 0.7605 0.8829
2.500 0.3948 0.04438 0.03314 -0.0721 0.7550 0.8870
2.750 0.4164 0.04492 0.03368 -0.0724 0.7474 0.8914
3.000 0.4513 0.04511 0.03387 -0.0741 0.7434 0.8954
3.250 0.4634 0.04580 0.03460 -0.0730 0.7341 0.8998
3.500 0.4962 0.04604 0.03486 -0.0745 0.7297 0.9041
3.750 0.5124 0.04684 0.03573 -0.0742 0.7207 0.9087
4.000 0.5417 0.04706 0.03599 -0.0750 0.7158 0.9132
4.250 0.5576 0.04785 0.03685 -0.0746 0.7070 0.9181
4.500 0.5882 0.04818 0.03725 -0.0758 0.7017 0.9228
4.750 0.6033 0.04894 0.03812 -0.0752 0.6927 0.9282
5.000 0.6340 0.04916 0.03842 -0.0763 0.6872 0.9337
5.250 0.6492 0.04993 0.03930 -0.0757 0.6772 0.9397
5.500 0.6834 0.04984 0.03934 -0.0769 0.6719 0.9462
5.750 0.6979 0.05060 0.04023 -0.0762 0.6607 0.9537
6.250 0.7491 0.05108 0.04098 -0.0771 0.6442 0.9774
6.500 0.7666 0.05183 0.04191 -0.0770 0.6325 0.9999
7.000 0.8279 0.05239 0.04279 -0.0794 0.6153 0.9999
7.250 0.8487 0.05322 0.04382 -0.0797 0.6033 0.9999
7.500 0.8738 0.05376 0.04453 -0.0803 0.5925 0.9999
7.750 0.9112 0.05333 0.04432 -0.0816 0.5854 0.9999
8.250 0.9531 0.05483 0.04626 -0.0819 0.5604 0.9999
8.500 0.9802 0.05476 0.04643 -0.0820 0.5481 0.9999
9.000 1.0394 0.05327 0.04544 -0.0815 0.5202 0.9999
9.250 1.0658 0.05269 0.04509 -0.0809 0.5031 0.9999
9.500 1.0951 0.05172 0.04434 -0.0803 0.4846 0.9999
9.750 1.1205 0.05115 0.04397 -0.0795 0.4625 0.9999
10.000 1.1468 0.05043 0.04341 -0.0785 0.4358 0.9999
10.250 1.1647 0.05071 0.04378 -0.0773 0.4038 0.9999
10.500 1.1799 0.05131 0.04437 -0.0760 0.3675 0.9999
10.750 1.1905 0.05244 0.04540 -0.0745 0.3284 0.9999
11.000 1.1971 0.05402 0.04675 -0.0729 0.2899 0.9999
11.250 1.1986 0.05640 0.04896 -0.0715 0.2554 0.9999
11.500 1.1981 0.05912 0.05153 -0.0703 0.2247 0.9999
11.750 1.1970 0.06204 0.05433 -0.0692 0.1985 0.9999
12.000 1.1968 0.06502 0.05724 -0.0684 0.1761 0.9999
12.250 1.1966 0.06804 0.06013 -0.0677 0.1583 0.9999
12.500 1.1977 0.07101 0.06305 -0.0670 0.1424 0.9999
12.750 1.2003 0.07386 0.06588 -0.0665 0.1291 0.9999
13.000 1.2036 0.07662 0.06862 -0.0660 0.1180 0.9999
13.250 1.2103 0.07913 0.07127 -0.0654 0.1076 0.9999
13.500 1.2171 0.08163 0.07386 -0.0648 0.0988 0.9999
13.750 1.2232 0.08406 0.07624 -0.0644 0.0913 0.9999
14.000 1.2332 0.08642 0.07891 -0.0638 0.0841 0.9999
14.250 1.2446 0.08831 0.08077 -0.0631 0.0781 0.9999
14.500 1.2487 0.09155 0.08442 -0.0630 0.0724 0.9999
14.750 1.2560 0.09407 0.08700 -0.0628 0.0676 0.9999
15.000 1.2630 0.09711 0.09030 -0.0624 0.0636 0.9999
15.250 1.2595 0.10143 0.09496 -0.0629 0.0600 0.9999
15.500 1.2581 0.10519 0.09885 -0.0637 0.0566 0.9999
15.750 1.2592 0.10881 0.10254 -0.0642 0.0535 0.9999
16.000 1.2453 0.11510 0.10925 -0.0664 0.0518 0.9999
16.250 1.2304 0.12178 0.11625 -0.0693 0.0503 0.9999
16.500 1.2140 0.12904 0.12380 -0.0731 0.0490 0.9999
16.750 1.1962 0.13710 0.13211 -0.0778 0.0484 0.9999
17.000 1.1729 0.14729 0.14254 -0.0842 0.0491 0.9999
17.250 1.1447 0.16008 0.15553 -0.0927 0.0507 0.9999
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