NACA 2412 (naca2412-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2412 (naca2412-il) Reynolds number: 50,000 Max Cl/Cd: 34.64 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2412-il-50000-n5.txt Download as CSV file: xf-naca2412-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2412
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5477 0.09827 0.09043 -0.0346 1.0000 0.0782
-10.500 -0.5580 0.09162 0.08383 -0.0383 1.0000 0.0780
-10.250 -0.5767 0.08302 0.07526 -0.0440 1.0000 0.0778
-10.000 -0.6041 0.07479 0.06704 -0.0499 1.0000 0.0775
-9.750 -0.6334 0.06891 0.06111 -0.0518 1.0000 0.0773
-9.500 -0.6585 0.06345 0.05549 -0.0524 1.0000 0.0774
-9.250 -0.6787 0.05847 0.05023 -0.0517 1.0000 0.0779
-9.000 -0.6907 0.05416 0.04558 -0.0503 1.0000 0.0788
-8.750 -0.6811 0.05224 0.04364 -0.0490 1.0000 0.0806
-8.500 -0.6748 0.04986 0.04112 -0.0474 1.0000 0.0823
-8.250 -0.6699 0.04702 0.03802 -0.0458 1.0000 0.0838
-8.000 -0.6633 0.04417 0.03483 -0.0442 1.0000 0.0854
-7.750 -0.6545 0.04150 0.03178 -0.0425 1.0000 0.0876
-7.500 -0.6442 0.03894 0.02866 -0.0408 1.0000 0.0908
-7.250 -0.6286 0.03734 0.02702 -0.0395 1.0000 0.0936
-7.000 -0.6122 0.03582 0.02538 -0.0381 1.0000 0.0968
-6.750 -0.5952 0.03412 0.02341 -0.0367 1.0000 0.1002
-6.500 -0.5772 0.03246 0.02133 -0.0353 1.0000 0.1047
-6.250 -0.5590 0.03135 0.02033 -0.0341 1.0000 0.1095
-6.000 -0.5399 0.03021 0.01901 -0.0329 1.0000 0.1160
-5.750 -0.5202 0.02904 0.01774 -0.0317 1.0000 0.1222
-5.500 -0.5006 0.02814 0.01678 -0.0305 1.0000 0.1308
-5.250 -0.4808 0.02726 0.01591 -0.0294 1.0000 0.1404
-5.000 -0.4605 0.02648 0.01506 -0.0284 1.0000 0.1526
-4.750 -0.4401 0.02578 0.01435 -0.0274 1.0000 0.1669
-4.500 -0.4197 0.02517 0.01378 -0.0264 1.0000 0.1837
-4.250 -0.3989 0.02461 0.01327 -0.0256 1.0000 0.2032
-4.000 -0.3774 0.02410 0.01278 -0.0249 1.0000 0.2269
-3.750 -0.3560 0.02364 0.01243 -0.0242 1.0000 0.2532
-3.500 -0.3346 0.02321 0.01211 -0.0236 1.0000 0.2838
-3.250 -0.3132 0.02282 0.01182 -0.0230 1.0000 0.3187
-3.000 -0.2815 0.02242 0.01161 -0.0243 0.9954 0.3657
-2.750 -0.2435 0.02203 0.01145 -0.0268 0.9869 0.4255
-2.500 -0.2072 0.02166 0.01141 -0.0287 0.9780 0.4958
-2.250 -0.1724 0.02136 0.01146 -0.0299 0.9689 0.5795
-2.000 -0.1388 0.02111 0.01156 -0.0303 0.9597 0.6724
-1.750 -0.1084 0.02097 0.01172 -0.0296 0.9492 0.7671
-1.500 -0.0638 0.02102 0.01188 -0.0315 0.9411 0.8665
-1.250 -0.0006 0.02114 0.01188 -0.0379 0.9339 0.9476
-1.000 0.0749 0.02117 0.01169 -0.0476 0.9291 1.0000
-0.750 0.1092 0.02114 0.01148 -0.0495 0.9152 1.0000
-0.500 0.1437 0.02113 0.01132 -0.0513 0.9017 1.0000
-0.250 0.1775 0.02111 0.01117 -0.0527 0.8883 1.0000
0.000 0.2112 0.02110 0.01104 -0.0540 0.8752 1.0000
0.250 0.2457 0.02106 0.01091 -0.0553 0.8626 1.0000
0.500 0.2790 0.02102 0.01079 -0.0562 0.8497 1.0000
0.750 0.3077 0.02104 0.01074 -0.0563 0.8350 1.0000
1.000 0.3361 0.02107 0.01071 -0.0562 0.8203 1.0000
1.250 0.3643 0.02111 0.01070 -0.0560 0.8056 1.0000
1.500 0.3924 0.02116 0.01071 -0.0558 0.7908 1.0000
1.750 0.4206 0.02122 0.01073 -0.0555 0.7761 1.0000
2.000 0.4485 0.02128 0.01076 -0.0552 0.7613 1.0000
2.250 0.4763 0.02135 0.01081 -0.0548 0.7464 1.0000
2.500 0.5037 0.02144 0.01088 -0.0543 0.7313 1.0000
2.750 0.5306 0.02155 0.01097 -0.0537 0.7159 1.0000
3.000 0.5571 0.02167 0.01108 -0.0530 0.7002 1.0000
3.250 0.5831 0.02182 0.01124 -0.0522 0.6841 1.0000
3.500 0.6086 0.02200 0.01141 -0.0514 0.6677 1.0000
3.750 0.6337 0.02220 0.01163 -0.0505 0.6509 1.0000
4.000 0.6585 0.02242 0.01186 -0.0495 0.6338 1.0000
4.250 0.6831 0.02266 0.01212 -0.0485 0.6163 1.0000
4.500 0.7074 0.02291 0.01241 -0.0475 0.5985 1.0000
4.750 0.7317 0.02318 0.01269 -0.0465 0.5805 1.0000
5.000 0.7558 0.02346 0.01300 -0.0454 0.5622 1.0000
5.250 0.7799 0.02375 0.01332 -0.0443 0.5435 1.0000
5.500 0.8039 0.02404 0.01362 -0.0432 0.5245 1.0000
5.750 0.8250 0.02445 0.01408 -0.0418 0.5030 1.0000
6.000 0.8459 0.02479 0.01443 -0.0402 0.4793 1.0000
6.250 0.8652 0.02516 0.01482 -0.0385 0.4534 1.0000
6.500 0.8841 0.02552 0.01513 -0.0366 0.4268 1.0000
6.750 0.9011 0.02602 0.01566 -0.0347 0.3983 1.0000
7.000 0.9177 0.02657 0.01622 -0.0327 0.3695 1.0000
7.250 0.9332 0.02719 0.01680 -0.0307 0.3394 1.0000
7.500 0.9472 0.02794 0.01747 -0.0286 0.3077 1.0000
7.750 0.9597 0.02884 0.01826 -0.0264 0.2758 1.0000
8.000 0.9709 0.02991 0.01920 -0.0242 0.2453 1.0000
8.250 0.9810 0.03115 0.02031 -0.0220 0.2177 1.0000
8.500 0.9904 0.03251 0.02155 -0.0199 0.1945 1.0000
8.750 0.9994 0.03396 0.02289 -0.0178 0.1752 1.0000
9.000 1.0085 0.03543 0.02431 -0.0157 0.1597 1.0000
9.250 1.0168 0.03694 0.02574 -0.0136 0.1475 1.0000
9.500 1.0277 0.03846 0.02736 -0.0119 0.1363 1.0000
9.750 1.0397 0.04004 0.02899 -0.0103 0.1276 1.0000
10.000 1.0506 0.04161 0.03054 -0.0087 0.1203 1.0000
10.250 1.0639 0.04329 0.03237 -0.0073 0.1133 1.0000
10.500 1.0779 0.04493 0.03405 -0.0061 0.1080 1.0000
10.750 1.0938 0.04673 0.03595 -0.0050 0.1033 1.0000
11.000 1.1055 0.04869 0.03815 -0.0038 0.0986 1.0000
11.250 1.1177 0.05050 0.04000 -0.0027 0.0946 1.0000
11.500 1.1318 0.05263 0.04222 -0.0017 0.0913 1.0000
11.750 1.1370 0.05529 0.04523 -0.0004 0.0886 1.0000
12.000 1.1398 0.05797 0.04817 0.0008 0.0859 1.0000
12.250 1.1430 0.06051 0.05089 0.0019 0.0833 1.0000
12.500 1.1537 0.06269 0.05305 0.0026 0.0807 1.0000
12.750 1.1467 0.06631 0.05694 0.0034 0.0793 1.0000
13.000 1.1314 0.07072 0.06171 0.0037 0.0784 1.0000
13.250 1.1122 0.07582 0.06713 0.0031 0.0776 1.0000
13.500 1.0885 0.08185 0.07346 0.0014 0.0772 1.0000
13.750 1.0588 0.08931 0.08118 -0.0017 0.0771 1.0000
14.000 1.0209 0.09902 0.09111 -0.0070 0.0775 1.0000
14.250 0.9730 0.11220 0.10447 -0.0150 0.0783 1.0000
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