NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2.5411 (naca2411-il) Reynolds number: 100,000 Max Cl/Cd: 52.24 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2411-il-100000-n5.txt Download as CSV file: xf-naca2411-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2.5411
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5748 0.06609 0.06065 -0.0586 1.0000 0.0380
-10.000 -0.6064 0.05974 0.05427 -0.0624 1.0000 0.0377
-9.750 -0.6382 0.05567 0.05010 -0.0608 1.0000 0.0376
-9.500 -0.6631 0.05147 0.04570 -0.0589 1.0000 0.0375
-9.250 -0.6828 0.04738 0.04130 -0.0563 1.0000 0.0376
-9.000 -0.6959 0.04351 0.03700 -0.0534 1.0000 0.0379
-8.750 -0.6981 0.04058 0.03378 -0.0508 1.0000 0.0383
-8.500 -0.6922 0.03862 0.03167 -0.0487 1.0000 0.0388
-8.250 -0.6838 0.03701 0.02992 -0.0466 1.0000 0.0397
-8.000 -0.6745 0.03539 0.02811 -0.0445 1.0000 0.0407
-7.750 -0.6643 0.03371 0.02618 -0.0425 1.0000 0.0423
-7.500 -0.6535 0.03178 0.02388 -0.0404 1.0000 0.0439
-7.250 -0.6409 0.02984 0.02148 -0.0384 1.0000 0.0453
-7.000 -0.6260 0.02838 0.01989 -0.0367 1.0000 0.0465
-6.750 -0.6098 0.02733 0.01878 -0.0352 1.0000 0.0479
-6.500 -0.5852 0.02629 0.01757 -0.0352 0.9978 0.0505
-6.250 -0.5524 0.02510 0.01600 -0.0366 0.9935 0.0543
-6.000 -0.5214 0.02408 0.01502 -0.0379 0.9886 0.0575
-5.750 -0.4876 0.02320 0.01398 -0.0395 0.9841 0.0620
-5.500 -0.4568 0.02234 0.01304 -0.0404 0.9785 0.0672
-5.250 -0.4232 0.02167 0.01228 -0.0419 0.9733 0.0737
-5.000 -0.3912 0.02098 0.01157 -0.0431 0.9677 0.0809
-4.750 -0.3591 0.02035 0.01086 -0.0441 0.9613 0.0898
-4.500 -0.3224 0.01980 0.01028 -0.0461 0.9567 0.1011
-4.250 -0.2945 0.01926 0.00977 -0.0463 0.9484 0.1128
-4.000 -0.2582 0.01874 0.00926 -0.0481 0.9432 0.1290
-3.750 -0.2293 0.01828 0.00884 -0.0485 0.9350 0.1464
-3.500 -0.1944 0.01779 0.00845 -0.0500 0.9291 0.1698
-3.250 -0.1642 0.01738 0.00812 -0.0505 0.9215 0.1959
-3.000 -0.1309 0.01696 0.00781 -0.0516 0.9148 0.2285
-2.750 -0.0976 0.01656 0.00752 -0.0527 0.9085 0.2674
-2.500 -0.0676 0.01617 0.00728 -0.0531 0.9003 0.3096
-2.250 -0.0321 0.01571 0.00700 -0.0546 0.8950 0.3638
-2.000 -0.0062 0.01529 0.00684 -0.0541 0.8849 0.4237
-1.750 0.0261 0.01476 0.00667 -0.0547 0.8783 0.5160
-1.500 0.0530 0.01430 0.00659 -0.0540 0.8686 0.6196
-1.250 0.0841 0.01389 0.00655 -0.0537 0.8609 0.7301
-1.000 0.1281 0.01365 0.00655 -0.0558 0.8533 0.8382
-0.750 0.1928 0.01352 0.00642 -0.0624 0.8489 0.9142
-0.500 0.2449 0.01349 0.00631 -0.0669 0.8386 0.9562
-0.250 0.2995 0.01339 0.00611 -0.0721 0.8294 0.9829
0.000 0.3510 0.01327 0.00589 -0.0769 0.8185 1.0000
0.250 0.3765 0.01322 0.00574 -0.0763 0.8037 1.0000
0.500 0.4020 0.01319 0.00561 -0.0757 0.7887 1.0000
0.750 0.4274 0.01318 0.00552 -0.0750 0.7734 1.0000
1.000 0.4526 0.01319 0.00544 -0.0743 0.7579 1.0000
1.250 0.4775 0.01323 0.00540 -0.0735 0.7423 1.0000
1.500 0.5022 0.01329 0.00539 -0.0726 0.7265 1.0000
1.750 0.5266 0.01337 0.00539 -0.0717 0.7105 1.0000
2.000 0.5507 0.01348 0.00543 -0.0707 0.6947 1.0000
2.250 0.5746 0.01360 0.00549 -0.0697 0.6788 1.0000
2.500 0.5982 0.01375 0.00557 -0.0687 0.6631 1.0000
2.750 0.6216 0.01391 0.00568 -0.0676 0.6474 1.0000
3.000 0.6448 0.01408 0.00582 -0.0665 0.6318 1.0000
3.250 0.6679 0.01428 0.00596 -0.0654 0.6162 1.0000
3.500 0.6907 0.01448 0.00613 -0.0642 0.6006 1.0000
3.750 0.7134 0.01470 0.00631 -0.0630 0.5847 1.0000
4.000 0.7358 0.01493 0.00653 -0.0618 0.5686 1.0000
4.250 0.7581 0.01517 0.00674 -0.0605 0.5523 1.0000
4.500 0.7801 0.01543 0.00697 -0.0592 0.5355 1.0000
4.750 0.8017 0.01569 0.00721 -0.0578 0.5178 1.0000
5.000 0.8226 0.01597 0.00748 -0.0563 0.4986 1.0000
5.250 0.8430 0.01625 0.00776 -0.0548 0.4781 1.0000
5.500 0.8630 0.01657 0.00803 -0.0531 0.4566 1.0000
5.750 0.8824 0.01689 0.00835 -0.0514 0.4333 1.0000
6.000 0.9009 0.01725 0.00866 -0.0496 0.4079 1.0000
6.250 0.9191 0.01763 0.00901 -0.0478 0.3799 1.0000
6.500 0.9362 0.01808 0.00940 -0.0458 0.3490 1.0000
6.750 0.9522 0.01861 0.00982 -0.0437 0.3161 1.0000
7.000 0.9673 0.01923 0.01032 -0.0415 0.2805 1.0000
7.250 0.9810 0.01997 0.01090 -0.0393 0.2436 1.0000
7.500 0.9935 0.02083 0.01157 -0.0369 0.2077 1.0000
7.750 1.0055 0.02175 0.01235 -0.0345 0.1749 1.0000
8.000 1.0167 0.02273 0.01319 -0.0321 0.1474 1.0000
8.250 1.0276 0.02374 0.01409 -0.0297 0.1259 1.0000
8.500 1.0371 0.02479 0.01504 -0.0271 0.1099 1.0000
8.750 1.0459 0.02578 0.01603 -0.0243 0.0976 1.0000
9.000 1.0546 0.02679 0.01705 -0.0216 0.0878 1.0000
9.250 1.0621 0.02789 0.01815 -0.0189 0.0798 1.0000
9.500 1.0692 0.02904 0.01932 -0.0163 0.0737 1.0000
9.750 1.0769 0.03023 0.02056 -0.0139 0.0681 1.0000
10.000 1.0842 0.03146 0.02184 -0.0116 0.0635 1.0000
10.250 1.0900 0.03288 0.02329 -0.0093 0.0598 1.0000
10.500 1.0982 0.03421 0.02474 -0.0074 0.0561 1.0000
10.750 1.1044 0.03567 0.02624 -0.0055 0.0530 1.0000
11.000 1.1100 0.03734 0.02792 -0.0037 0.0508 1.0000
11.250 1.1188 0.03890 0.02965 -0.0021 0.0484 1.0000
11.500 1.1264 0.04054 0.03140 -0.0007 0.0461 1.0000
11.750 1.1325 0.04227 0.03318 0.0006 0.0442 1.0000
12.000 1.1386 0.04418 0.03510 0.0018 0.0426 1.0000
12.250 1.1463 0.04608 0.03723 0.0030 0.0409 1.0000
12.500 1.1533 0.04813 0.03945 0.0040 0.0395 1.0000
12.750 1.1593 0.05028 0.04174 0.0049 0.0384 1.0000
13.000 1.1646 0.05250 0.04408 0.0057 0.0375 1.0000
13.250 1.1688 0.05478 0.04645 0.0064 0.0365 1.0000
13.500 1.1739 0.05715 0.04885 0.0069 0.0356 1.0000
13.750 1.1728 0.06021 0.05215 0.0073 0.0349 1.0000
14.000 1.1676 0.06370 0.05594 0.0073 0.0341 1.0000
14.250 1.1610 0.06746 0.05995 0.0070 0.0333 1.0000
14.500 1.1530 0.07152 0.06424 0.0063 0.0328 1.0000
14.750 1.1426 0.07605 0.06900 0.0051 0.0323 1.0000
15.000 1.1303 0.08105 0.07423 0.0034 0.0320 1.0000
15.250 1.1151 0.08675 0.08016 0.0011 0.0318 1.0000
15.500 1.0967 0.09331 0.08695 -0.0021 0.0317 1.0000
15.750 1.0733 0.10124 0.09512 -0.0064 0.0318 1.0000
16.000 1.0428 0.11123 0.10537 -0.0124 0.0319 1.0000
16.250 0.9885 0.12817 0.12259 -0.0235 0.0327 1.0000
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