ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 13% AIRFOIL (arad13-il) Reynolds number: 200,000 Max Cl/Cd: 56.07 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad13-il-200000.txt Download as CSV file: xf-arad13-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 13% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3013 0.09380 0.09051 -0.0203 1.0000 0.0731
-8.750 -0.3466 0.08513 0.08189 -0.0298 1.0000 0.0756
-8.500 -0.5324 0.05831 0.05443 -0.0449 1.0000 0.0488
-8.250 -0.5199 0.05600 0.05212 -0.0449 1.0000 0.0491
-8.000 -0.5196 0.04873 0.04456 -0.0469 1.0000 0.0477
-7.750 -0.5323 0.03456 0.02913 -0.0496 1.0000 0.0471
-7.500 -0.5180 0.02918 0.02277 -0.0497 1.0000 0.0491
-7.250 -0.4945 0.02878 0.02258 -0.0491 1.0000 0.0505
-7.000 -0.4754 0.02730 0.02092 -0.0481 1.0000 0.0522
-6.750 -0.4612 0.02513 0.01817 -0.0462 1.0000 0.0543
-6.500 -0.4519 0.02433 0.01740 -0.0436 1.0000 0.0557
-6.250 -0.4102 0.02345 0.01645 -0.0466 0.9950 0.0592
-6.000 -0.3683 0.02222 0.01507 -0.0496 0.9894 0.0631
-5.750 -0.3248 0.02124 0.01378 -0.0527 0.9839 0.0679
-5.500 -0.2831 0.02042 0.01311 -0.0557 0.9769 0.0723
-5.250 -0.2416 0.01948 0.01204 -0.0583 0.9689 0.0776
-5.000 -0.2035 0.01896 0.01146 -0.0602 0.9566 0.0829
-4.750 -0.1689 0.01829 0.01080 -0.0613 0.9423 0.0880
-4.500 -0.1378 0.01793 0.01030 -0.0614 0.9258 0.0936
-4.250 -0.1108 0.01741 0.00983 -0.0607 0.9084 0.0987
-4.000 -0.0845 0.01718 0.00945 -0.0597 0.8908 0.1048
-3.750 -0.0591 0.01672 0.00904 -0.0587 0.8738 0.1107
-3.500 -0.0328 0.01656 0.00871 -0.0577 0.8571 0.1178
-3.250 -0.0070 0.01612 0.00834 -0.0568 0.8410 0.1253
-3.000 0.0195 0.01581 0.00793 -0.0560 0.8247 0.1341
-2.750 0.0468 0.01560 0.00769 -0.0554 0.8074 0.1438
-2.500 0.0742 0.01526 0.00736 -0.0549 0.7905 0.1541
-2.250 0.1021 0.01501 0.00706 -0.0545 0.7743 0.1660
-2.000 0.1301 0.01485 0.00685 -0.0541 0.7589 0.1790
-1.750 0.1580 0.01458 0.00659 -0.0538 0.7441 0.1935
-1.500 0.1862 0.01435 0.00636 -0.0535 0.7290 0.2101
-1.250 0.2148 0.01411 0.00616 -0.0534 0.7132 0.2301
-1.000 0.2434 0.01387 0.00597 -0.0533 0.6980 0.2561
-0.750 0.2716 0.01350 0.00579 -0.0533 0.6832 0.3003
-0.500 0.2950 0.01215 0.00572 -0.0525 0.6695 0.6306
-0.250 0.3257 0.01113 0.00544 -0.0510 0.6537 1.0000
0.000 0.3539 0.01122 0.00534 -0.0508 0.6378 1.0000
0.250 0.3821 0.01133 0.00528 -0.0506 0.6220 1.0000
0.500 0.4104 0.01144 0.00523 -0.0505 0.6065 1.0000
0.750 0.4387 0.01158 0.00520 -0.0503 0.5909 1.0000
1.000 0.4671 0.01172 0.00517 -0.0502 0.5749 1.0000
1.250 0.4955 0.01187 0.00517 -0.0501 0.5580 1.0000
1.500 0.5240 0.01202 0.00519 -0.0500 0.5404 1.0000
1.750 0.5525 0.01218 0.00523 -0.0500 0.5224 1.0000
2.000 0.5808 0.01237 0.00528 -0.0499 0.5037 1.0000
2.250 0.6090 0.01258 0.00534 -0.0499 0.4841 1.0000
2.500 0.6373 0.01279 0.00544 -0.0498 0.4636 1.0000
2.750 0.6655 0.01303 0.00556 -0.0498 0.4425 1.0000
3.000 0.6934 0.01330 0.00569 -0.0498 0.4209 1.0000
3.250 0.7212 0.01360 0.00585 -0.0498 0.3998 1.0000
3.500 0.7488 0.01394 0.00604 -0.0497 0.3799 1.0000
3.750 0.7762 0.01431 0.00626 -0.0497 0.3615 1.0000
4.000 0.8037 0.01468 0.00652 -0.0496 0.3444 1.0000
4.250 0.8310 0.01507 0.00680 -0.0496 0.3290 1.0000
4.500 0.8583 0.01549 0.00711 -0.0496 0.3155 1.0000
4.750 0.8851 0.01596 0.00744 -0.0495 0.3037 1.0000
5.000 0.9122 0.01636 0.00778 -0.0495 0.2924 1.0000
5.250 0.9392 0.01680 0.00817 -0.0494 0.2824 1.0000
5.500 0.9658 0.01729 0.00855 -0.0493 0.2736 1.0000
5.750 0.9927 0.01772 0.00897 -0.0492 0.2651 1.0000
6.000 1.0191 0.01820 0.00936 -0.0491 0.2574 1.0000
6.250 1.0456 0.01870 0.00985 -0.0490 0.2504 1.0000
6.500 1.0720 0.01912 0.01027 -0.0489 0.2436 1.0000
6.750 1.0978 0.01977 0.01079 -0.0487 0.2375 1.0000
7.000 1.1240 0.02016 0.01127 -0.0485 0.2314 1.0000
7.250 1.1497 0.02065 0.01173 -0.0483 0.2259 1.0000
7.500 1.1751 0.02132 0.01234 -0.0482 0.2207 1.0000
7.750 1.2005 0.02176 0.01287 -0.0479 0.2154 1.0000
8.000 1.2256 0.02227 0.01336 -0.0476 0.2106 1.0000
8.250 1.2506 0.02308 0.01406 -0.0475 0.2060 1.0000
8.500 1.2748 0.02353 0.01466 -0.0470 0.2015 1.0000
8.750 1.2989 0.02405 0.01522 -0.0467 0.1969 1.0000
9.000 1.3231 0.02469 0.01581 -0.0463 0.1930 1.0000
9.250 1.3468 0.02549 0.01664 -0.0460 0.1891 1.0000
9.500 1.3693 0.02605 0.01733 -0.0454 0.1849 1.0000
9.750 1.3920 0.02663 0.01794 -0.0448 0.1810 1.0000
10.000 1.4154 0.02741 0.01863 -0.0445 0.1775 1.0000
10.250 1.4369 0.02827 0.01960 -0.0439 0.1741 1.0000
10.500 1.4569 0.02894 0.02042 -0.0429 0.1705 1.0000
10.750 1.4774 0.02960 0.02112 -0.0422 0.1671 1.0000
11.000 1.4989 0.03035 0.02182 -0.0416 0.1640 1.0000
11.250 1.5198 0.03145 0.02296 -0.0410 0.1609 1.0000
11.500 1.5351 0.03227 0.02398 -0.0395 0.1579 1.0000
11.750 1.5514 0.03307 0.02488 -0.0382 0.1548 1.0000
12.000 1.5689 0.03382 0.02566 -0.0372 0.1521 1.0000
12.250 1.5904 0.03484 0.02659 -0.0368 0.1494 1.0000
12.500 1.6024 0.03604 0.02796 -0.0351 0.1470 1.0000
12.750 1.6093 0.03711 0.02924 -0.0326 0.1445 1.0000
13.000 1.6165 0.03816 0.03042 -0.0303 0.1421 1.0000
13.250 1.6252 0.03916 0.03148 -0.0282 0.1399 1.0000
13.500 1.6393 0.04014 0.03243 -0.0269 0.1378 1.0000
13.750 1.6561 0.04163 0.03392 -0.0262 0.1354 1.0000
14.000 1.6504 0.04334 0.03589 -0.0231 0.1338 1.0000
14.250 1.6469 0.04526 0.03802 -0.0209 0.1320 1.0000
14.500 1.6470 0.04715 0.04008 -0.0193 0.1300 1.0000
14.750 1.6511 0.04888 0.04189 -0.0181 0.1282 1.0000
15.000 1.6611 0.05025 0.04328 -0.0173 0.1263 1.0000
15.250 1.6807 0.05142 0.04436 -0.0169 0.1241 1.0000
15.500 1.6696 0.05450 0.04769 -0.0157 0.1228 1.0000
15.750 1.6555 0.05804 0.05149 -0.0149 0.1214 1.0000
16.000 1.6412 0.06191 0.05560 -0.0147 0.1200 1.0000
16.250 1.6293 0.06579 0.05968 -0.0149 0.1185 1.0000
16.500 1.6222 0.06926 0.06328 -0.0153 0.1170 1.0000
16.750 1.6246 0.07170 0.06577 -0.0155 0.1154 1.0000
17.000 1.6431 0.07237 0.06635 -0.0149 0.1136 1.0000
17.250 1.6336 0.07653 0.07064 -0.0155 0.1122 1.0000
17.500 1.5931 0.08458 0.07903 -0.0182 0.1114 1.0000
17.750 1.5368 0.09599 0.09081 -0.0234 0.1107 1.0000
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