NACA 2410 (naca2410-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2410 (naca2410-il) Reynolds number: 50,000 Max Cl/Cd: 36.08 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2410-il-50000-n5.txt Download as CSV file: xf-naca2410-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2410
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5281 0.09780 0.09035 -0.0247 1.0000 0.0669
-9.500 -0.5327 0.09260 0.08522 -0.0275 1.0000 0.0666
-9.250 -0.5395 0.08706 0.07975 -0.0308 1.0000 0.0665
-9.000 -0.5500 0.08089 0.07366 -0.0352 1.0000 0.0664
-8.750 -0.5646 0.07404 0.06684 -0.0402 1.0000 0.0662
-8.500 -0.5783 0.06772 0.06048 -0.0435 1.0000 0.0663
-8.250 -0.5897 0.06196 0.05453 -0.0454 1.0000 0.0669
-8.000 -0.5969 0.05664 0.04892 -0.0463 1.0000 0.0679
-7.750 -0.5999 0.05161 0.04346 -0.0462 1.0000 0.0692
-7.500 -0.5976 0.04702 0.03831 -0.0456 1.0000 0.0703
-7.250 -0.5880 0.04363 0.03455 -0.0446 1.0000 0.0719
-7.000 -0.5725 0.04197 0.03285 -0.0436 1.0000 0.0753
-6.750 -0.5581 0.03956 0.03012 -0.0425 1.0000 0.0788
-6.500 -0.5426 0.03671 0.02675 -0.0414 1.0000 0.0814
-6.250 -0.5247 0.03417 0.02364 -0.0403 1.0000 0.0844
-6.000 -0.5058 0.03280 0.02230 -0.0393 1.0000 0.0887
-5.750 -0.4858 0.03123 0.02044 -0.0383 1.0000 0.0935
-5.500 -0.4641 0.02950 0.01829 -0.0372 1.0000 0.0973
-5.250 -0.4429 0.02812 0.01687 -0.0363 1.0000 0.1012
-5.000 -0.4214 0.02707 0.01570 -0.0353 1.0000 0.1083
-4.750 -0.3997 0.02603 0.01459 -0.0343 1.0000 0.1164
-4.500 -0.3773 0.02506 0.01344 -0.0333 1.0000 0.1254
-4.250 -0.3551 0.02414 0.01255 -0.0324 1.0000 0.1358
-4.000 -0.3325 0.02337 0.01176 -0.0316 1.0000 0.1532
-3.750 -0.3097 0.02263 0.01109 -0.0310 1.0000 0.1757
-3.500 -0.2874 0.02196 0.01051 -0.0304 1.0000 0.2070
-3.250 -0.2650 0.02136 0.01007 -0.0299 1.0000 0.2494
-3.000 -0.2428 0.02076 0.00971 -0.0293 1.0000 0.3017
-2.750 -0.2207 0.02017 0.00940 -0.0287 1.0000 0.3646
-2.500 -0.1990 0.01960 0.00921 -0.0279 1.0000 0.4437
-2.250 -0.1790 0.01905 0.00917 -0.0264 1.0000 0.5487
-2.000 -0.1620 0.01859 0.00925 -0.0236 1.0000 0.6772
-1.750 -0.1412 0.01832 0.00938 -0.0209 1.0000 0.8391
-1.500 -0.0892 0.01833 0.00923 -0.0260 0.9953 1.0000
-1.250 -0.0452 0.01857 0.00913 -0.0299 0.9850 1.0000
-1.000 -0.0023 0.01879 0.00909 -0.0336 0.9741 1.0000
-0.750 0.0392 0.01899 0.00906 -0.0369 0.9624 1.0000
-0.500 0.0792 0.01916 0.00906 -0.0398 0.9499 1.0000
-0.250 0.1181 0.01932 0.00908 -0.0424 0.9370 1.0000
0.000 0.1571 0.01946 0.00910 -0.0449 0.9241 1.0000
0.250 0.1968 0.01958 0.00914 -0.0474 0.9115 1.0000
0.500 0.2368 0.01967 0.00916 -0.0498 0.8991 1.0000
0.750 0.2749 0.01973 0.00916 -0.0517 0.8862 1.0000
1.000 0.3099 0.01978 0.00919 -0.0530 0.8720 1.0000
1.250 0.3432 0.01983 0.00923 -0.0538 0.8572 1.0000
1.500 0.3757 0.01987 0.00926 -0.0545 0.8421 1.0000
1.750 0.4065 0.01993 0.00933 -0.0547 0.8263 1.0000
2.000 0.4360 0.02000 0.00942 -0.0546 0.8097 1.0000
2.250 0.4649 0.02009 0.00953 -0.0544 0.7929 1.0000
2.500 0.4934 0.02018 0.00965 -0.0541 0.7757 1.0000
2.750 0.5219 0.02027 0.00978 -0.0538 0.7584 1.0000
3.000 0.5502 0.02038 0.00993 -0.0533 0.7408 1.0000
3.250 0.5783 0.02048 0.01007 -0.0527 0.7230 1.0000
3.500 0.6063 0.02059 0.01021 -0.0521 0.7050 1.0000
3.750 0.6315 0.02081 0.01050 -0.0512 0.6846 1.0000
4.000 0.6573 0.02100 0.01074 -0.0503 0.6642 1.0000
4.250 0.6840 0.02115 0.01093 -0.0493 0.6440 1.0000
4.500 0.7078 0.02143 0.01129 -0.0481 0.6208 1.0000
4.750 0.7332 0.02162 0.01150 -0.0470 0.5979 1.0000
5.000 0.7560 0.02191 0.01184 -0.0455 0.5712 1.0000
5.250 0.7784 0.02218 0.01216 -0.0440 0.5423 1.0000
5.500 0.7999 0.02248 0.01247 -0.0423 0.5106 1.0000
5.750 0.8205 0.02283 0.01279 -0.0405 0.4764 1.0000
6.000 0.8393 0.02326 0.01322 -0.0386 0.4371 1.0000
6.250 0.8562 0.02378 0.01366 -0.0364 0.3899 1.0000
6.500 0.8710 0.02449 0.01416 -0.0342 0.3336 1.0000
6.750 0.8846 0.02549 0.01487 -0.0320 0.2729 1.0000
7.000 0.8971 0.02683 0.01586 -0.0301 0.2178 1.0000
7.250 0.9094 0.02840 0.01715 -0.0283 0.1759 1.0000
7.500 0.9226 0.03001 0.01861 -0.0266 0.1485 1.0000
7.750 0.9365 0.03162 0.02013 -0.0249 0.1303 1.0000
8.000 0.9511 0.03319 0.02166 -0.0234 0.1167 1.0000
8.250 0.9664 0.03470 0.02319 -0.0219 0.1062 1.0000
8.500 0.9851 0.03627 0.02490 -0.0206 0.0990 1.0000
8.750 1.0044 0.03789 0.02660 -0.0195 0.0935 1.0000
9.000 1.0257 0.03967 0.02851 -0.0186 0.0884 1.0000
9.250 1.0445 0.04141 0.03046 -0.0176 0.0827 1.0000
9.500 1.0645 0.04332 0.03231 -0.0169 0.0785 1.0000
9.750 1.0844 0.04573 0.03509 -0.0159 0.0756 1.0000
10.250 1.1105 0.05035 0.04033 -0.0133 0.0687 1.0000
10.500 1.1254 0.05280 0.04278 -0.0125 0.0659 1.0000
10.750 1.1283 0.05603 0.04647 -0.0105 0.0644 1.0000
11.000 1.1240 0.05936 0.05026 -0.0082 0.0629 1.0000
11.250 1.1143 0.06264 0.05390 -0.0058 0.0615 1.0000
11.500 1.1019 0.06617 0.05773 -0.0039 0.0603 1.0000
11.750 1.0869 0.07008 0.06191 -0.0029 0.0594 1.0000
12.000 1.0684 0.07464 0.06672 -0.0028 0.0589 1.0000
12.250 1.0444 0.08032 0.07265 -0.0043 0.0589 1.0000
12.500 1.0122 0.08797 0.08054 -0.0079 0.0596 1.0000
12.750 0.9747 0.09801 0.09076 -0.0141 0.0610 1.0000
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Polar data table (+)
Polar graphs
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