FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-158 AIRFOIL (fx63158-il) Reynolds number: 50,000 Max Cl/Cd: 18.81 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63158-il-50000-n5.txt Download as CSV file: xf-fx63158-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-158 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3089 0.11104 0.10437 -0.0513 1.0000 0.0599
-10.000 -0.3269 0.10443 0.09789 -0.0554 1.0000 0.0535
-9.750 -0.3213 0.10199 0.09553 -0.0541 1.0000 0.0524
-9.500 -0.3237 0.09859 0.09224 -0.0541 1.0000 0.0509
-9.000 -0.3635 0.08763 0.08150 -0.0587 1.0000 0.0461
-8.750 -0.3771 0.08501 0.07901 -0.0577 1.0000 0.0456
-8.500 -0.3987 0.08282 0.07695 -0.0558 1.0000 0.0451
-8.250 -0.4076 0.07850 0.07263 -0.0595 0.9916 0.0442
-8.000 -0.4091 0.07238 0.06632 -0.0674 0.9725 0.0428
-7.750 -0.4154 0.06562 0.05897 -0.0748 0.9491 0.0404
-7.500 -0.3994 0.06134 0.05448 -0.0782 0.9348 0.0398
-7.250 -0.3810 0.05707 0.04989 -0.0816 0.9219 0.0390
-7.000 -0.3604 0.05309 0.04552 -0.0845 0.9093 0.0383
-6.750 -0.3391 0.04943 0.04141 -0.0866 0.8963 0.0376
-6.500 -0.3111 0.04591 0.03737 -0.0889 0.8864 0.0372
-6.250 -0.2799 0.04276 0.03372 -0.0910 0.8771 0.0369
-6.000 -0.2497 0.04024 0.03077 -0.0922 0.8670 0.0369
-5.750 -0.2139 0.03791 0.02803 -0.0937 0.8592 0.0372
-5.500 -0.1832 0.03614 0.02597 -0.0939 0.8493 0.0378
-5.250 -0.1459 0.03450 0.02407 -0.0945 0.8424 0.0387
-5.000 -0.1156 0.03345 0.02278 -0.0935 0.8328 0.0400
-4.750 -0.0820 0.03231 0.02156 -0.0932 0.8253 0.0427
-4.500 -0.0565 0.03150 0.02060 -0.0923 0.8152 0.0460
-4.250 -0.0274 0.03041 0.01947 -0.0927 0.8071 0.0497
-4.000 -0.0053 0.02963 0.01858 -0.0923 0.7966 0.0539
-3.750 0.0252 0.02858 0.01749 -0.0935 0.7891 0.0640
-3.500 0.0464 0.02773 0.01671 -0.0934 0.7786 0.0828
-3.250 0.0639 0.02483 0.01601 -0.0942 0.7714 0.3992
-3.000 0.0709 0.02734 0.01893 -0.0856 0.7610 0.6364
-2.750 0.0889 0.02911 0.02044 -0.0797 0.7542 0.6901
-2.500 0.0992 0.03011 0.02128 -0.0739 0.7455 0.7184
-2.250 0.1192 0.03058 0.02150 -0.0706 0.7389 0.7423
-2.000 0.1399 0.03077 0.02146 -0.0681 0.7324 0.7601
-1.750 0.1568 0.03088 0.02138 -0.0661 0.7246 0.7743
-1.250 0.2013 0.03079 0.02088 -0.0646 0.7122 0.7920
-1.000 0.2226 0.03075 0.02068 -0.0636 0.7061 0.7983
-0.750 0.2523 0.03062 0.02034 -0.0644 0.7017 0.8059
-0.500 0.2648 0.03081 0.02045 -0.0624 0.6948 0.8120
-0.250 0.2862 0.03085 0.02036 -0.0619 0.6890 0.8173
0.000 0.3178 0.03075 0.02007 -0.0631 0.6847 0.8220
0.250 0.3299 0.03103 0.02030 -0.0613 0.6774 0.8276
0.500 0.3509 0.03108 0.02025 -0.0605 0.6714 0.8333
0.750 0.3836 0.03098 0.02000 -0.0616 0.6671 0.8388
1.000 0.3929 0.03146 0.02047 -0.0597 0.6594 0.8439
1.250 0.4150 0.03157 0.02052 -0.0592 0.6537 0.8477
1.500 0.4482 0.03151 0.02034 -0.0604 0.6497 0.8513
1.750 0.4555 0.03223 0.02109 -0.0585 0.6423 0.8556
2.000 0.4793 0.03261 0.02142 -0.0589 0.6368 0.8590
2.250 0.5097 0.03260 0.02136 -0.0596 0.6330 0.8622
2.500 0.5163 0.03339 0.02219 -0.0573 0.6260 0.8669
2.750 0.5345 0.03392 0.02272 -0.0568 0.6202 0.8716
3.000 0.5674 0.03406 0.02283 -0.0582 0.6165 0.8754
3.250 0.5781 0.03490 0.02372 -0.0568 0.6100 0.8787
3.500 0.5918 0.03570 0.02458 -0.0558 0.6033 0.8817
3.750 0.6250 0.03583 0.02469 -0.0572 0.5994 0.8840
4.250 0.6514 0.03776 0.02673 -0.0557 0.5851 0.8904
4.500 0.6884 0.03779 0.02680 -0.0574 0.5815 0.8932
4.750 0.6762 0.03973 0.02885 -0.0539 0.5714 0.8973
5.000 0.7046 0.04003 0.02919 -0.0545 0.5665 0.9001
5.250 0.7470 0.03971 0.02890 -0.0565 0.5634 0.9024
5.500 0.7317 0.04242 0.03173 -0.0537 0.5515 0.9064
6.000 0.7561 0.04514 0.03466 -0.0530 0.5367 0.9137
6.250 0.7863 0.04522 0.03483 -0.0535 0.5320 0.9176
6.500 0.8312 0.04431 0.03399 -0.0549 0.5289 0.9211
6.750 0.8101 0.04809 0.03791 -0.0530 0.5154 0.9266
7.000 0.8587 0.04642 0.03635 -0.0539 0.5120 0.9303
7.250 0.8434 0.04992 0.03997 -0.0526 0.4982 0.9365
7.500 0.8947 0.04781 0.03798 -0.0534 0.4950 0.9414
7.750 0.8779 0.05172 0.04203 -0.0526 0.4810 0.9496
8.000 0.9295 0.04945 0.03991 -0.0532 0.4779 0.9571
8.250 0.9100 0.05385 0.04445 -0.0529 0.4631 0.9778
8.750 0.9487 0.05601 0.04692 -0.0543 0.4451 1.0000
9.250 0.9897 0.05795 0.04916 -0.0556 0.4279 1.0000
9.500 0.9857 0.06177 0.05312 -0.0565 0.4142 1.0000
10.000 1.0224 0.06414 0.05583 -0.0577 0.3961 1.0000
10.500 1.0266 0.07049 0.06247 -0.0596 0.3706 1.0000
10.750 1.0596 0.06953 0.06172 -0.0596 0.3637 1.0000
11.000 1.0631 0.07256 0.06491 -0.0605 0.3513 1.0000
11.250 1.1067 0.07007 0.06264 -0.0602 0.3462 1.0000
11.500 1.1013 0.07429 0.06701 -0.0613 0.3319 1.0000
12.000 1.1081 0.08038 0.07344 -0.0630 0.3057 1.0000
12.250 1.1367 0.07962 0.07286 -0.0628 0.2960 1.0000
12.500 1.1621 0.07934 0.07278 -0.0627 0.2851 1.0000
13.000 1.1692 0.08528 0.07901 -0.0643 0.2541 1.0000
13.250 1.1892 0.08543 0.07921 -0.0641 0.2367 1.0000
13.500 1.1995 0.08716 0.08092 -0.0644 0.2171 1.0000
13.750 1.1975 0.09104 0.08486 -0.0656 0.1971 1.0000
14.000 1.2063 0.09291 0.08652 -0.0659 0.1784 1.0000
14.250 1.2070 0.09641 0.08994 -0.0669 0.1621 1.0000
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Polar data table (+)
Polar graphs
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