S4180-098-84 (s4180-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S4180-098-84 (s4180-il) Reynolds number: 100,000 Max Cl/Cd: 58.75 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4180-il-100000-n5.txt Download as CSV file: xf-s4180-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4180-098-84
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2838 0.09046 0.08584 -0.0308 1.0000 0.0581
-7.500 -0.2814 0.08783 0.08329 -0.0311 1.0000 0.0585
-7.250 -0.2843 0.08553 0.08110 -0.0309 1.0000 0.0587
-6.750 -0.2775 0.07350 0.06911 -0.0449 0.9798 0.0379
-6.500 -0.2523 0.06954 0.06514 -0.0494 0.9682 0.0370
-6.250 -0.2253 0.06419 0.05973 -0.0577 0.9542 0.0364
-6.000 -0.1968 0.05793 0.05334 -0.0673 0.9395 0.0366
-5.750 -0.1688 0.05181 0.04702 -0.0754 0.9255 0.0366
-5.500 -0.1424 0.04614 0.04110 -0.0814 0.9116 0.0360
-5.250 -0.1172 0.04048 0.03508 -0.0861 0.8975 0.0352
-5.000 -0.0914 0.03502 0.02909 -0.0897 0.8842 0.0348
-4.750 -0.0648 0.03076 0.02425 -0.0917 0.8718 0.0348
-4.500 -0.0375 0.02753 0.02043 -0.0928 0.8603 0.0352
-4.250 -0.0100 0.02512 0.01747 -0.0931 0.8487 0.0364
-4.000 0.0174 0.02320 0.01499 -0.0931 0.8361 0.0384
-3.750 0.0440 0.02210 0.01375 -0.0929 0.8240 0.0399
-3.500 0.0712 0.02094 0.01236 -0.0925 0.8125 0.0413
-3.250 0.0984 0.01987 0.01105 -0.0920 0.8009 0.0432
-3.000 0.1256 0.01892 0.00986 -0.0915 0.7884 0.0456
-2.750 0.1523 0.01825 0.00916 -0.0911 0.7763 0.0496
-2.500 0.1795 0.01767 0.00842 -0.0905 0.7648 0.0558
-2.250 0.2063 0.01704 0.00779 -0.0900 0.7532 0.0631
-2.000 0.2334 0.01655 0.00725 -0.0896 0.7407 0.0770
-1.750 0.2605 0.01617 0.00687 -0.0892 0.7288 0.0979
-1.500 0.2875 0.01588 0.00659 -0.0889 0.7175 0.1265
-1.250 0.3145 0.01554 0.00627 -0.0885 0.7059 0.1546
-1.000 0.3415 0.01522 0.00602 -0.0881 0.6938 0.1904
-0.750 0.3684 0.01485 0.00582 -0.0878 0.6825 0.2558
-0.500 0.3948 0.01430 0.00570 -0.0875 0.6718 0.4054
-0.250 0.4157 0.01352 0.00573 -0.0856 0.6606 0.6678
0.000 0.4422 0.01294 0.00552 -0.0840 0.6495 1.0000
0.250 0.4699 0.01308 0.00540 -0.0837 0.6389 1.0000
0.500 0.4976 0.01322 0.00534 -0.0834 0.6280 1.0000
0.750 0.5252 0.01339 0.00533 -0.0832 0.6170 1.0000
1.000 0.5527 0.01356 0.00531 -0.0829 0.6069 1.0000
1.250 0.5802 0.01373 0.00533 -0.0826 0.5967 1.0000
1.500 0.6077 0.01393 0.00540 -0.0824 0.5861 1.0000
1.750 0.6351 0.01412 0.00545 -0.0821 0.5769 1.0000
2.000 0.6624 0.01433 0.00556 -0.0819 0.5666 1.0000
2.250 0.6897 0.01455 0.00568 -0.0817 0.5569 1.0000
2.500 0.7170 0.01477 0.00578 -0.0814 0.5482 1.0000
2.750 0.7441 0.01501 0.00598 -0.0812 0.5380 1.0000
3.000 0.7712 0.01525 0.00612 -0.0809 0.5294 1.0000
3.250 0.7981 0.01550 0.00634 -0.0807 0.5197 1.0000
3.500 0.8250 0.01576 0.00655 -0.0804 0.5105 1.0000
3.750 0.8518 0.01602 0.00674 -0.0801 0.5017 1.0000
4.000 0.8784 0.01629 0.00703 -0.0799 0.4918 1.0000
4.250 0.9050 0.01657 0.00725 -0.0795 0.4829 1.0000
4.500 0.9313 0.01685 0.00753 -0.0792 0.4728 1.0000
4.750 0.9575 0.01715 0.00785 -0.0789 0.4629 1.0000
5.000 0.9836 0.01743 0.00807 -0.0785 0.4535 1.0000
5.250 1.0092 0.01774 0.00843 -0.0782 0.4424 1.0000
5.500 1.0348 0.01805 0.00876 -0.0778 0.4317 1.0000
5.750 1.0602 0.01836 0.00907 -0.0773 0.4213 1.0000
6.000 1.0853 0.01869 0.00943 -0.0769 0.4097 1.0000
6.250 1.1100 0.01903 0.00982 -0.0764 0.3977 1.0000
6.500 1.1345 0.01938 0.01023 -0.0759 0.3855 1.0000
6.750 1.1585 0.01974 0.01061 -0.0753 0.3728 1.0000
7.000 1.1821 0.02012 0.01101 -0.0747 0.3593 1.0000
7.250 1.2051 0.02053 0.01147 -0.0740 0.3449 1.0000
7.500 1.2276 0.02097 0.01196 -0.0733 0.3295 1.0000
7.750 1.2494 0.02145 0.01248 -0.0725 0.3132 1.0000
8.000 1.2706 0.02199 0.01305 -0.0717 0.2960 1.0000
8.250 1.2908 0.02259 0.01368 -0.0708 0.2779 1.0000
8.500 1.3098 0.02327 0.01436 -0.0698 0.2599 1.0000
8.750 1.3274 0.02405 0.01511 -0.0687 0.2417 1.0000
9.000 1.3442 0.02490 0.01596 -0.0675 0.2236 1.0000
9.250 1.3593 0.02585 0.01692 -0.0662 0.2064 1.0000
9.500 1.3727 0.02690 0.01796 -0.0647 0.1907 1.0000
9.750 1.3844 0.02802 0.01909 -0.0631 0.1769 1.0000
10.000 1.3943 0.02923 0.02030 -0.0613 0.1650 1.0000
10.250 1.3999 0.03053 0.02159 -0.0590 0.1551 1.0000
10.500 1.4057 0.03189 0.02302 -0.0570 0.1458 1.0000
10.750 1.4103 0.03340 0.02458 -0.0551 0.1379 1.0000
11.000 1.4133 0.03512 0.02634 -0.0534 0.1310 1.0000
11.250 1.4174 0.03688 0.02818 -0.0520 0.1249 1.0000
11.500 1.4203 0.03885 0.03021 -0.0508 0.1191 1.0000
11.750 1.4219 0.04102 0.03241 -0.0498 0.1144 1.0000
12.000 1.4259 0.04310 0.03465 -0.0489 0.1093 1.0000
12.250 1.4273 0.04548 0.03709 -0.0483 0.1051 1.0000
12.500 1.4291 0.04793 0.03957 -0.0477 0.1016 1.0000
12.750 1.4326 0.05030 0.04211 -0.0473 0.0977 1.0000
13.000 1.4345 0.05290 0.04482 -0.0470 0.0943 1.0000
13.250 1.4353 0.05565 0.04759 -0.0469 0.0914 1.0000
13.500 1.4375 0.05834 0.05039 -0.0468 0.0885 1.0000
13.750 1.4396 0.06117 0.05342 -0.0468 0.0855 1.0000
14.000 1.4408 0.06409 0.05647 -0.0470 0.0830 1.0000
14.250 1.4415 0.06712 0.05958 -0.0473 0.0807 1.0000
14.500 1.4445 0.06982 0.06226 -0.0473 0.0784 1.0000
14.750 1.4433 0.07336 0.06604 -0.0480 0.0764 1.0000
15.000 1.4416 0.07701 0.06991 -0.0487 0.0743 1.0000
15.250 1.4399 0.08073 0.07379 -0.0496 0.0723 1.0000
15.500 1.4389 0.08437 0.07756 -0.0506 0.0705 1.0000
15.750 1.4390 0.08788 0.08114 -0.0515 0.0689 1.0000
16.000 1.4434 0.09064 0.08391 -0.0518 0.0671 1.0000
16.250 1.4341 0.09601 0.08958 -0.0540 0.0659 1.0000
16.500 1.4234 0.10172 0.09555 -0.0565 0.0646 1.0000
16.750 1.4120 0.10774 0.10181 -0.0594 0.0634 1.0000
17.000 1.3998 0.11402 0.10831 -0.0625 0.0622 1.0000
17.250 1.3870 0.12066 0.11514 -0.0661 0.0611 1.0000
17.500 1.3730 0.12764 0.12229 -0.0700 0.0602 1.0000
17.750 1.3589 0.13489 0.12970 -0.0742 0.0593 1.0000
18.000 1.3484 0.14145 0.13639 -0.0781 0.0584 1.0000
18.250 1.3645 0.14173 0.13660 -0.0775 0.0568 1.0000
18.500 1.3188 0.15729 0.15244 -0.0881 0.0567 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S4180-098-84 (s4180-il)