S4180-098-84 (s4180-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S4180-098-84 (s4180-il) Reynolds number: 200,000 Max Cl/Cd: 78.73 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4180-il-200000-n5.txt Download as CSV file: xf-s4180-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2547 0.11202 0.10865 -0.0219 1.0000 0.0312
-10.250 -0.2560 0.10863 0.10529 -0.0240 1.0000 0.0314
-10.000 -0.2562 0.10504 0.10173 -0.0259 1.0000 0.0315
-9.750 -0.2536 0.10119 0.09789 -0.0279 1.0000 0.0316
-9.500 -0.2512 0.09740 0.09413 -0.0294 1.0000 0.0316
-9.250 -0.2406 0.09365 0.09042 -0.0288 1.0000 0.0320
-9.000 -0.2300 0.09043 0.08722 -0.0288 1.0000 0.0324
-8.750 -0.2244 0.08717 0.08399 -0.0295 1.0000 0.0327
-8.500 -0.2183 0.08397 0.08082 -0.0303 1.0000 0.0333
-8.250 -0.2092 0.08064 0.07751 -0.0320 0.9833 0.0349
-8.000 -0.1989 0.07604 0.07291 -0.0362 0.9602 0.0365
-7.500 -0.2817 0.08186 0.07863 -0.0328 0.9950 0.0330
-7.250 -0.2704 0.07224 0.06898 -0.0464 0.9540 0.0263
-7.000 -0.2482 0.06952 0.06622 -0.0492 0.9362 0.0252
-6.750 -0.2307 0.06511 0.06175 -0.0550 0.9153 0.0244
-6.250 -0.2083 0.04331 0.03945 -0.0785 0.8744 0.0212
-6.000 -0.1926 0.03399 0.02957 -0.0845 0.8604 0.0210
-5.750 -0.1726 0.02691 0.02159 -0.0879 0.8481 0.0211
-5.500 -0.1487 0.02384 0.01798 -0.0888 0.8357 0.0217
-5.250 -0.1235 0.02266 0.01659 -0.0889 0.8237 0.0224
-5.000 -0.0977 0.02127 0.01491 -0.0889 0.8121 0.0231
-4.750 -0.0713 0.01958 0.01281 -0.0888 0.8007 0.0236
-4.500 -0.0443 0.01820 0.01110 -0.0887 0.7887 0.0240
-4.250 -0.0172 0.01709 0.00970 -0.0885 0.7772 0.0246
-4.000 0.0100 0.01618 0.00854 -0.0882 0.7660 0.0252
-3.750 0.0374 0.01544 0.00759 -0.0879 0.7540 0.0259
-3.500 0.0647 0.01476 0.00682 -0.0877 0.7421 0.0268
-3.250 0.0922 0.01435 0.00635 -0.0874 0.7303 0.0285
-3.000 0.1197 0.01394 0.00582 -0.0872 0.7188 0.0306
-2.750 0.1475 0.01348 0.00526 -0.0870 0.7068 0.0324
-2.500 0.1754 0.01313 0.00485 -0.0868 0.6949 0.0348
-2.250 0.2034 0.01281 0.00444 -0.0866 0.6834 0.0387
-2.000 0.2313 0.01253 0.00410 -0.0864 0.6720 0.0469
-1.750 0.2593 0.01228 0.00387 -0.0863 0.6601 0.0627
-1.500 0.2873 0.01212 0.00368 -0.0861 0.6487 0.0795
-1.250 0.3152 0.01198 0.00354 -0.0860 0.6376 0.0988
-1.000 0.3430 0.01184 0.00344 -0.0859 0.6265 0.1289
-0.750 0.3710 0.01167 0.00333 -0.0859 0.6151 0.1608
-0.500 0.3990 0.01150 0.00324 -0.0858 0.6044 0.2063
-0.250 0.4267 0.01129 0.00318 -0.0858 0.5940 0.2832
0.000 0.4540 0.01092 0.00320 -0.0858 0.5832 0.4185
0.250 0.4791 0.01042 0.00326 -0.0852 0.5734 0.6139
0.500 0.4959 0.00989 0.00329 -0.0820 0.5642 0.8471
0.750 0.5282 0.00980 0.00319 -0.0824 0.5537 1.0000
1.000 0.5562 0.00994 0.00318 -0.0823 0.5443 1.0000
1.250 0.5842 0.01009 0.00320 -0.0822 0.5346 1.0000
1.500 0.6122 0.01023 0.00324 -0.0821 0.5253 1.0000
2.000 0.6679 0.01055 0.00336 -0.0819 0.5071 1.0000
2.250 0.6956 0.01073 0.00344 -0.0817 0.4987 1.0000
2.500 0.7233 0.01089 0.00354 -0.0816 0.4895 1.0000
2.750 0.7510 0.01107 0.00365 -0.0815 0.4811 1.0000
3.000 0.7785 0.01126 0.00377 -0.0813 0.4722 1.0000
3.250 0.8060 0.01144 0.00392 -0.0812 0.4635 1.0000
3.500 0.8332 0.01166 0.00405 -0.0810 0.4548 1.0000
3.750 0.8606 0.01184 0.00422 -0.0809 0.4454 1.0000
4.000 0.8876 0.01206 0.00439 -0.0807 0.4365 1.0000
4.250 0.9147 0.01227 0.00458 -0.0805 0.4266 1.0000
4.500 0.9416 0.01248 0.00477 -0.0803 0.4170 1.0000
4.750 0.9682 0.01273 0.00498 -0.0800 0.4075 1.0000
5.000 0.9950 0.01295 0.00520 -0.0799 0.3971 1.0000
5.250 1.0214 0.01319 0.00544 -0.0796 0.3870 1.0000
5.500 1.0475 0.01347 0.00568 -0.0793 0.3765 1.0000
5.750 1.0737 0.01372 0.00595 -0.0791 0.3647 1.0000
6.000 1.0996 0.01399 0.00622 -0.0788 0.3525 1.0000
6.250 1.1251 0.01429 0.00651 -0.0784 0.3395 1.0000
6.500 1.1503 0.01462 0.00683 -0.0781 0.3255 1.0000
6.750 1.1751 0.01496 0.00716 -0.0777 0.3104 1.0000
7.000 1.1995 0.01535 0.00752 -0.0773 0.2943 1.0000
7.250 1.2233 0.01577 0.00793 -0.0768 0.2776 1.0000
7.500 1.2466 0.01625 0.00836 -0.0762 0.2602 1.0000
7.750 1.2690 0.01679 0.00885 -0.0756 0.2420 1.0000
8.000 1.2911 0.01736 0.00939 -0.0750 0.2230 1.0000
8.250 1.3123 0.01799 0.00997 -0.0742 0.2052 1.0000
8.500 1.3326 0.01868 0.01062 -0.0734 0.1881 1.0000
8.750 1.3519 0.01943 0.01132 -0.0725 0.1720 1.0000
9.000 1.3705 0.02021 0.01207 -0.0715 0.1574 1.0000
9.250 1.3887 0.02099 0.01284 -0.0705 0.1447 1.0000
9.500 1.4061 0.02179 0.01365 -0.0693 0.1336 1.0000
9.750 1.4221 0.02265 0.01451 -0.0681 0.1238 1.0000
10.000 1.4359 0.02360 0.01546 -0.0666 0.1151 1.0000
10.250 1.4499 0.02446 0.01638 -0.0650 0.1076 1.0000
10.500 1.4587 0.02548 0.01742 -0.0629 0.1018 1.0000
10.750 1.4684 0.02646 0.01847 -0.0609 0.0964 1.0000
11.000 1.4744 0.02772 0.01976 -0.0589 0.0915 1.0000
11.250 1.4820 0.02896 0.02109 -0.0572 0.0875 1.0000
11.500 1.4891 0.03034 0.02255 -0.0557 0.0836 1.0000
11.750 1.4935 0.03201 0.02427 -0.0543 0.0803 1.0000
12.000 1.4971 0.03384 0.02617 -0.0531 0.0775 1.0000
12.250 1.5037 0.03553 0.02799 -0.0521 0.0746 1.0000
12.500 1.5080 0.03750 0.03006 -0.0513 0.0719 1.0000
12.750 1.5101 0.03978 0.03240 -0.0507 0.0695 1.0000
13.000 1.5094 0.04245 0.03514 -0.0502 0.0675 1.0000
13.250 1.5130 0.04478 0.03759 -0.0499 0.0657 1.0000
13.500 1.5160 0.04721 0.04017 -0.0497 0.0638 1.0000
13.750 1.5179 0.04988 0.04296 -0.0497 0.0619 1.0000
14.000 1.5179 0.05281 0.04599 -0.0498 0.0601 1.0000
14.250 1.5163 0.05604 0.04929 -0.0502 0.0586 1.0000
14.500 1.5128 0.05955 0.05287 -0.0506 0.0572 1.0000
14.750 1.5127 0.06272 0.05616 -0.0510 0.0560 1.0000
15.000 1.5133 0.06588 0.05948 -0.0515 0.0548 1.0000
15.250 1.5132 0.06924 0.06299 -0.0522 0.0534 1.0000
15.500 1.5123 0.07279 0.06667 -0.0531 0.0521 1.0000
15.750 1.5107 0.07654 0.07053 -0.0542 0.0509 1.0000
16.000 1.5081 0.08048 0.07457 -0.0554 0.0497 1.0000
16.250 1.5048 0.08461 0.07878 -0.0567 0.0486 1.0000
16.500 1.5015 0.08866 0.08286 -0.0579 0.0475 1.0000
16.750 1.5000 0.09272 0.08711 -0.0594 0.0466 1.0000
17.000 1.4976 0.09693 0.09149 -0.0610 0.0455 1.0000
17.250 1.4948 0.10132 0.09604 -0.0627 0.0444 1.0000
17.500 1.4913 0.10586 0.10073 -0.0647 0.0434 1.0000
17.750 1.4869 0.11064 0.10564 -0.0669 0.0423 1.0000
18.000 1.4819 0.11558 0.11069 -0.0693 0.0412 1.0000
18.250 1.4773 0.12053 0.11570 -0.0718 0.0402 1.0000
18.500 1.4730 0.12526 0.12048 -0.0742 0.0391 1.0000
18.750 1.4661 0.13086 0.12629 -0.0772 0.0382 1.0000
19.000 1.4589 0.13659 0.13219 -0.0805 0.0372 1.0000
19.250 1.4517 0.14239 0.13816 -0.0839 0.0362 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S4180-098-84 (s4180-il)