NACA 2410 (naca2410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2410 (naca2410-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.73 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2410-il-1000000-n5.txt Download as CSV file: xf-naca2410-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.9011 0.10848 0.10636 -0.0108 1.0000 0.0069
-15.500 -1.0391 0.07950 0.07709 -0.0278 1.0000 0.0063
-15.250 -1.2124 0.03950 0.03642 -0.0604 1.0000 0.0057
-15.000 -1.2259 0.03501 0.03174 -0.0631 1.0000 0.0057
-14.750 -1.2312 0.03253 0.02911 -0.0623 1.0000 0.0058
-14.500 -1.2286 0.03066 0.02710 -0.0610 1.0000 0.0058
-14.250 -1.2195 0.02907 0.02537 -0.0601 1.0000 0.0059
-14.000 -1.2073 0.02768 0.02386 -0.0593 1.0000 0.0060
-13.750 -1.1966 0.02601 0.02205 -0.0583 1.0000 0.0062
-13.500 -1.1824 0.02466 0.02057 -0.0574 1.0000 0.0064
-13.250 -1.1661 0.02352 0.01933 -0.0565 1.0000 0.0066
-13.000 -1.1485 0.02251 0.01823 -0.0557 1.0000 0.0068
-12.750 -1.1301 0.02160 0.01723 -0.0548 1.0000 0.0070
-12.500 -1.1112 0.02075 0.01629 -0.0539 1.0000 0.0072
-12.250 -1.0920 0.01998 0.01542 -0.0529 1.0000 0.0075
-12.000 -1.0728 0.01925 0.01461 -0.0518 1.0000 0.0077
-11.750 -1.0533 0.01858 0.01384 -0.0507 1.0000 0.0079
-11.500 -1.0334 0.01796 0.01314 -0.0496 1.0000 0.0081
-11.250 -1.0142 0.01727 0.01237 -0.0484 1.0000 0.0084
-11.000 -0.9949 0.01661 0.01165 -0.0471 1.0000 0.0088
-10.750 -0.9752 0.01604 0.01102 -0.0459 1.0000 0.0092
-10.500 -0.9495 0.01547 0.01040 -0.0459 0.9993 0.0096
-10.250 -0.9199 0.01494 0.00979 -0.0467 0.9980 0.0102
-10.000 -0.8898 0.01446 0.00924 -0.0475 0.9966 0.0107
-9.750 -0.8596 0.01390 0.00864 -0.0483 0.9953 0.0115
-9.500 -0.8290 0.01341 0.00811 -0.0493 0.9941 0.0125
-9.250 -0.7998 0.01299 0.00765 -0.0498 0.9921 0.0134
-9.000 -0.7696 0.01260 0.00720 -0.0505 0.9901 0.0141
-8.750 -0.7389 0.01219 0.00679 -0.0514 0.9884 0.0157
-8.500 -0.7074 0.01185 0.00644 -0.0524 0.9868 0.0172
-8.250 -0.6758 0.01154 0.00609 -0.0533 0.9852 0.0186
-8.000 -0.6467 0.01124 0.00580 -0.0537 0.9819 0.0204
-7.750 -0.6170 0.01099 0.00554 -0.0542 0.9783 0.0219
-7.500 -0.5860 0.01075 0.00527 -0.0550 0.9751 0.0231
-7.250 -0.5571 0.01053 0.00501 -0.0552 0.9697 0.0239
-7.000 -0.5280 0.01021 0.00468 -0.0555 0.9637 0.0256
-6.750 -0.4999 0.00997 0.00443 -0.0556 0.9573 0.0269
-6.500 -0.4720 0.00977 0.00420 -0.0556 0.9504 0.0281
-6.250 -0.4443 0.00958 0.00398 -0.0555 0.9436 0.0291
-6.000 -0.4169 0.00940 0.00376 -0.0553 0.9355 0.0298
-5.750 -0.3895 0.00923 0.00354 -0.0552 0.9274 0.0305
-5.500 -0.3626 0.00896 0.00323 -0.0549 0.9183 0.0322
-5.250 -0.3355 0.00876 0.00300 -0.0547 0.9087 0.0337
-5.000 -0.3083 0.00859 0.00279 -0.0545 0.8986 0.0352
-4.750 -0.2811 0.00844 0.00260 -0.0542 0.8875 0.0364
-4.500 -0.2536 0.00831 0.00242 -0.0541 0.8758 0.0374
-4.250 -0.2262 0.00819 0.00224 -0.0539 0.8635 0.0386
-4.000 -0.1988 0.00804 0.00206 -0.0537 0.8506 0.0422
-3.750 -0.1714 0.00792 0.00191 -0.0535 0.8370 0.0461
-3.500 -0.1441 0.00779 0.00177 -0.0533 0.8226 0.0537
-3.250 -0.1168 0.00766 0.00163 -0.0532 0.8075 0.0658
-3.000 -0.0894 0.00755 0.00152 -0.0530 0.7919 0.0794
-2.750 -0.0619 0.00745 0.00142 -0.0529 0.7759 0.0926
-2.500 -0.0344 0.00737 0.00132 -0.0527 0.7589 0.1069
-2.250 -0.0069 0.00729 0.00124 -0.0526 0.7420 0.1233
-2.000 0.0206 0.00723 0.00117 -0.0525 0.7245 0.1415
-1.750 0.0480 0.00715 0.00111 -0.0524 0.7071 0.1628
-1.250 0.1028 0.00695 0.00101 -0.0522 0.6720 0.2321
-1.000 0.1303 0.00688 0.00098 -0.0522 0.6538 0.2630
-0.750 0.1579 0.00684 0.00096 -0.0521 0.6358 0.2894
-0.250 0.2125 0.00665 0.00094 -0.0520 0.6002 0.3830
0.000 0.2398 0.00658 0.00095 -0.0519 0.5828 0.4290
0.250 0.2668 0.00646 0.00096 -0.0518 0.5656 0.4950
0.500 0.2936 0.00631 0.00099 -0.0516 0.5484 0.5720
0.750 0.3207 0.00623 0.00103 -0.0515 0.5316 0.6289
1.000 0.3477 0.00618 0.00108 -0.0513 0.5157 0.6801
1.250 0.3745 0.00613 0.00113 -0.0510 0.5001 0.7301
1.500 0.4007 0.00607 0.00119 -0.0506 0.4841 0.7846
1.750 0.4262 0.00601 0.00127 -0.0500 0.4685 0.8423
2.000 0.4506 0.00601 0.00136 -0.0490 0.4507 0.8950
2.250 0.4751 0.00616 0.00146 -0.0481 0.4154 0.9381
2.500 0.5050 0.00643 0.00157 -0.0486 0.3720 0.9664
2.750 0.5375 0.00669 0.00168 -0.0497 0.3371 0.9825
3.000 0.5706 0.00692 0.00179 -0.0509 0.3096 0.9926
3.250 0.6045 0.00722 0.00194 -0.0525 0.2735 1.0000
3.500 0.6286 0.00758 0.00211 -0.0518 0.2342 1.0000
3.750 0.6529 0.00793 0.00229 -0.0512 0.1972 1.0000
4.000 0.6775 0.00827 0.00249 -0.0506 0.1656 1.0000
4.250 0.7025 0.00860 0.00269 -0.0502 0.1384 1.0000
4.500 0.7275 0.00894 0.00291 -0.0497 0.1137 1.0000
4.750 0.7526 0.00927 0.00313 -0.0492 0.0930 1.0000
5.000 0.7780 0.00957 0.00336 -0.0488 0.0768 1.0000
5.250 0.8031 0.00991 0.00361 -0.0484 0.0593 1.0000
5.500 0.8281 0.01028 0.00388 -0.0479 0.0446 1.0000
5.750 0.8539 0.01054 0.00412 -0.0476 0.0395 1.0000
6.000 0.8795 0.01083 0.00438 -0.0472 0.0355 1.0000
6.250 0.9055 0.01107 0.00463 -0.0469 0.0339 1.0000
6.500 0.9313 0.01132 0.00489 -0.0466 0.0327 1.0000
6.750 0.9569 0.01159 0.00518 -0.0462 0.0314 1.0000
7.000 0.9822 0.01189 0.00548 -0.0459 0.0299 1.0000
7.250 1.0071 0.01223 0.00582 -0.0454 0.0284 1.0000
7.500 1.0319 0.01258 0.00620 -0.0449 0.0270 1.0000
7.750 1.0573 0.01284 0.00648 -0.0446 0.0265 1.0000
8.000 1.0824 0.01312 0.00679 -0.0442 0.0258 1.0000
8.250 1.1073 0.01342 0.00712 -0.0438 0.0250 1.0000
8.500 1.1319 0.01375 0.00746 -0.0434 0.0240 1.0000
8.750 1.1560 0.01410 0.00782 -0.0429 0.0228 1.0000
9.000 1.1795 0.01452 0.00826 -0.0423 0.0216 1.0000
9.250 1.2029 0.01492 0.00869 -0.0417 0.0208 1.0000
9.500 1.2271 0.01523 0.00904 -0.0412 0.0201 1.0000
9.750 1.2509 0.01556 0.00940 -0.0407 0.0191 1.0000
10.000 1.2741 0.01593 0.00978 -0.0401 0.0178 1.0000
10.250 1.2966 0.01636 0.01022 -0.0394 0.0165 1.0000
10.500 1.3188 0.01680 0.01069 -0.0386 0.0155 1.0000
10.750 1.3406 0.01724 0.01116 -0.0379 0.0144 1.0000
11.000 1.3617 0.01773 0.01165 -0.0370 0.0130 1.0000
11.250 1.3820 0.01827 0.01221 -0.0360 0.0118 1.0000
11.500 1.4018 0.01881 0.01281 -0.0350 0.0110 1.0000
11.750 1.4205 0.01942 0.01344 -0.0338 0.0101 1.0000
12.000 1.4380 0.02008 0.01414 -0.0325 0.0093 1.0000
12.250 1.4549 0.02073 0.01485 -0.0311 0.0088 1.0000
12.500 1.4696 0.02138 0.01556 -0.0292 0.0084 1.0000
12.750 1.4829 0.02209 0.01633 -0.0273 0.0081 1.0000
13.000 1.4950 0.02288 0.01718 -0.0253 0.0077 1.0000
13.250 1.5061 0.02376 0.01813 -0.0233 0.0073 1.0000
13.500 1.5158 0.02476 0.01920 -0.0213 0.0070 1.0000
13.750 1.5240 0.02592 0.02043 -0.0193 0.0066 1.0000
14.000 1.5336 0.02699 0.02159 -0.0176 0.0065 1.0000
14.250 1.5423 0.02819 0.02287 -0.0160 0.0063 1.0000
14.500 1.5499 0.02953 0.02430 -0.0145 0.0061 1.0000
14.750 1.5565 0.03101 0.02587 -0.0131 0.0059 1.0000
15.000 1.5618 0.03269 0.02764 -0.0120 0.0058 1.0000
15.250 1.5660 0.03456 0.02960 -0.0110 0.0056 1.0000
15.500 1.5688 0.03666 0.03181 -0.0102 0.0054 1.0000
15.750 1.5701 0.03906 0.03430 -0.0096 0.0053 1.0000
16.000 1.5696 0.04175 0.03709 -0.0094 0.0052 1.0000
16.250 1.5673 0.04480 0.04025 -0.0094 0.0050 1.0000
16.500 1.5628 0.04827 0.04384 -0.0098 0.0049 1.0000
16.750 1.5557 0.05222 0.04791 -0.0106 0.0048 1.0000
17.000 1.5460 0.05670 0.05253 -0.0118 0.0048 1.0000
17.250 1.5377 0.06116 0.05711 -0.0132 0.0047 1.0000
17.500 1.5267 0.06616 0.06224 -0.0150 0.0047 1.0000
17.750 1.5136 0.07167 0.06789 -0.0171 0.0047 1.0000
18.000 1.4975 0.07781 0.07416 -0.0196 0.0046 1.0000
18.250 1.4790 0.08449 0.08098 -0.0225 0.0046 1.0000
18.500 1.4576 0.09188 0.08852 -0.0259 0.0046 1.0000
18.750 1.4323 0.10014 0.09692 -0.0298 0.0046 1.0000
19.000 1.4054 0.10896 0.10590 -0.0341 0.0046 1.0000
19.250 1.3745 0.11881 0.11590 -0.0390 0.0046 1.0000
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