LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LDS-2 AIRFOIL (lds2-il) Reynolds number: 50,000 Max Cl/Cd: 33.27 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lds2-il-50000-n5.txt Download as CSV file: xf-lds2-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LDS-2 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 -0.4425 0.09988 0.09234 -0.0396 1.0000 0.0616
-10.000 -0.4465 0.09510 0.08763 -0.0418 1.0000 0.0604
-9.500 -0.5101 0.07748 0.07008 -0.0560 1.0000 0.0550
-9.250 -0.5215 0.07409 0.06672 -0.0558 1.0000 0.0547
-9.000 -0.5384 0.07072 0.06335 -0.0548 1.0000 0.0545
-8.750 -0.5529 0.06739 0.05996 -0.0535 1.0000 0.0544
-8.500 -0.5652 0.06419 0.05668 -0.0517 1.0000 0.0542
-8.250 -0.5753 0.06113 0.05349 -0.0495 1.0000 0.0540
-8.000 -0.5834 0.05824 0.05045 -0.0470 1.0000 0.0538
-7.750 -0.5900 0.05544 0.04745 -0.0442 1.0000 0.0537
-7.500 -0.5948 0.05272 0.04448 -0.0413 1.0000 0.0537
-7.250 -0.5964 0.05017 0.04165 -0.0384 1.0000 0.0537
-7.000 -0.5958 0.04765 0.03881 -0.0356 1.0000 0.0539
-6.750 -0.5927 0.04527 0.03605 -0.0329 1.0000 0.0544
-6.500 -0.5873 0.04315 0.03346 -0.0302 1.0000 0.0552
-6.250 -0.5778 0.04108 0.03134 -0.0284 1.0000 0.0566
-6.000 -0.5665 0.03947 0.02963 -0.0265 1.0000 0.0583
-5.750 -0.5447 0.03751 0.02736 -0.0264 0.9967 0.0600
-5.500 -0.5132 0.03538 0.02483 -0.0276 0.9903 0.0616
-5.250 -0.4795 0.03360 0.02264 -0.0290 0.9843 0.0645
-5.000 -0.4483 0.03205 0.02089 -0.0300 0.9776 0.0680
-4.750 -0.4153 0.03071 0.01947 -0.0312 0.9719 0.0719
-4.500 -0.3837 0.02960 0.01817 -0.0319 0.9651 0.0766
-4.250 -0.3518 0.02853 0.01708 -0.0330 0.9591 0.0831
-4.000 -0.3229 0.02766 0.01606 -0.0333 0.9517 0.0905
-3.750 -0.2901 0.02671 0.01510 -0.0347 0.9458 0.1025
-3.500 -0.2639 0.02584 0.01420 -0.0349 0.9377 0.1186
-3.250 -0.2317 0.02449 0.01320 -0.0366 0.9321 0.1675
-3.000 -0.2168 0.02272 0.01299 -0.0351 0.9241 0.4352
-2.750 -0.1925 0.02243 0.01312 -0.0337 0.9173 0.5811
-2.500 -0.1746 0.02232 0.01345 -0.0304 0.9099 0.6876
-2.250 -0.1514 0.02247 0.01396 -0.0268 0.9038 0.7922
-2.000 -0.1063 0.02262 0.01397 -0.0290 0.9000 0.8380
-1.750 -0.0642 0.02274 0.01388 -0.0316 0.8941 0.8682
-1.500 -0.0136 0.02287 0.01380 -0.0361 0.8893 0.8981
-1.250 0.0461 0.02297 0.01366 -0.0424 0.8860 0.9249
-1.000 0.1084 0.02300 0.01347 -0.0494 0.8832 0.9489
-0.750 0.1603 0.02307 0.01338 -0.0549 0.8772 0.9748
-0.500 0.2189 0.02304 0.01318 -0.0618 0.8727 0.9993
-0.250 0.2446 0.02304 0.01304 -0.0623 0.8652 1.0000
0.000 0.2587 0.02320 0.01309 -0.0607 0.8546 1.0000
0.250 0.2788 0.02338 0.01315 -0.0599 0.8456 1.0000
0.500 0.3032 0.02352 0.01319 -0.0597 0.8371 1.0000
0.750 0.3211 0.02380 0.01338 -0.0583 0.8275 1.0000
1.000 0.3490 0.02395 0.01346 -0.0585 0.8201 1.0000
1.250 0.3649 0.02433 0.01378 -0.0567 0.8103 1.0000
1.500 0.3940 0.02449 0.01391 -0.0570 0.8035 1.0000
1.750 0.4089 0.02494 0.01432 -0.0550 0.7935 1.0000
2.000 0.4391 0.02510 0.01447 -0.0554 0.7870 1.0000
2.250 0.4538 0.02557 0.01494 -0.0534 0.7763 1.0000
2.500 0.4872 0.02556 0.01493 -0.0539 0.7686 1.0000
2.750 0.5078 0.02575 0.01514 -0.0524 0.7561 1.0000
3.000 0.5289 0.02593 0.01535 -0.0509 0.7435 1.0000
3.250 0.5547 0.02597 0.01542 -0.0500 0.7320 1.0000
3.500 0.5886 0.02570 0.01520 -0.0500 0.7217 1.0000
3.750 0.6110 0.02568 0.01526 -0.0484 0.7069 1.0000
4.000 0.6356 0.02552 0.01514 -0.0469 0.6913 1.0000
4.250 0.6608 0.02530 0.01498 -0.0455 0.6751 1.0000
4.500 0.6864 0.02504 0.01478 -0.0440 0.6582 1.0000
4.750 0.7060 0.02498 0.01481 -0.0418 0.6387 1.0000
5.000 0.7259 0.02487 0.01478 -0.0396 0.6172 1.0000
5.250 0.7506 0.02451 0.01445 -0.0378 0.5941 1.0000
5.500 0.7669 0.02452 0.01455 -0.0351 0.5660 1.0000
5.750 0.7850 0.02448 0.01453 -0.0327 0.5341 1.0000
6.000 0.8013 0.02454 0.01457 -0.0300 0.4952 1.0000
6.250 0.8178 0.02467 0.01456 -0.0274 0.4474 1.0000
6.500 0.8331 0.02504 0.01462 -0.0246 0.3943 1.0000
6.750 0.8433 0.02586 0.01509 -0.0217 0.3430 1.0000
7.000 0.8516 0.02694 0.01582 -0.0188 0.3031 1.0000
7.250 0.8601 0.02812 0.01676 -0.0162 0.2713 1.0000
7.500 0.8689 0.02930 0.01780 -0.0137 0.2451 1.0000
7.750 0.8786 0.03048 0.01885 -0.0114 0.2246 1.0000
8.000 0.8895 0.03168 0.01992 -0.0094 0.2073 1.0000
8.250 0.9025 0.03287 0.02104 -0.0076 0.1920 1.0000
8.500 0.9183 0.03404 0.02221 -0.0062 0.1787 1.0000
8.750 0.9353 0.03523 0.02343 -0.0050 0.1667 1.0000
9.000 0.9548 0.03644 0.02463 -0.0041 0.1566 1.0000
9.250 0.9763 0.03765 0.02586 -0.0035 0.1475 1.0000
9.500 0.9972 0.03896 0.02734 -0.0028 0.1388 1.0000
9.750 1.0198 0.04026 0.02858 -0.0024 0.1319 1.0000
10.000 1.0408 0.04185 0.03044 -0.0018 0.1253 1.0000
10.250 1.0596 0.04329 0.03193 -0.0010 0.1196 1.0000
10.500 1.0782 0.04504 0.03386 -0.0003 0.1146 1.0000
10.750 1.0926 0.04698 0.03607 0.0008 0.1102 1.0000
11.000 1.1076 0.04869 0.03788 0.0018 0.1061 1.0000
11.250 1.1213 0.05068 0.03996 0.0027 0.1025 1.0000
11.500 1.1215 0.05315 0.04281 0.0049 0.0996 1.0000
11.750 1.1228 0.05571 0.04567 0.0066 0.0971 1.0000
12.000 1.1244 0.05824 0.04843 0.0081 0.0948 1.0000
12.250 1.1298 0.06050 0.05079 0.0092 0.0925 1.0000
12.500 1.1335 0.06309 0.05346 0.0102 0.0903 1.0000
12.750 1.1136 0.06700 0.05773 0.0117 0.0893 1.0000
13.000 1.0904 0.07155 0.06260 0.0123 0.0885 1.0000
13.250 1.0634 0.07695 0.06828 0.0119 0.0880 1.0000
13.500 1.0310 0.08361 0.07519 0.0100 0.0879 1.0000
13.750 0.9893 0.09250 0.08428 0.0060 0.0882 1.0000
14.000 0.9393 0.10465 0.09655 -0.0008 0.0889 1.0000
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Polar data table (+)
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