NACA 2410 (naca2410-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2410 (naca2410-il) Reynolds number: 100,000 Max Cl/Cd: 51.76 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2410-il-100000.txt Download as CSV file: xf-naca2410-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4926 0.10044 0.09529 -0.0166 1.0000 0.1359
-9.000 -0.5244 0.09690 0.09192 -0.0249 1.0000 0.1412
-8.750 -0.5087 0.09219 0.08720 -0.0225 1.0000 0.1440
-8.500 -0.4935 0.08934 0.08431 -0.0206 1.0000 0.1496
-8.250 -0.5189 0.08540 0.08053 -0.0266 1.0000 0.1553
-8.000 -0.5171 0.08102 0.07618 -0.0269 1.0000 0.1593
-7.750 -0.5088 0.07839 0.07356 -0.0260 1.0000 0.1677
-7.500 -0.5812 0.05456 0.04896 -0.0447 1.0000 0.0992
-7.250 -0.5721 0.05033 0.04461 -0.0437 1.0000 0.0958
-7.000 -0.5676 0.04563 0.03963 -0.0428 1.0000 0.0941
-6.750 -0.5621 0.04058 0.03413 -0.0416 1.0000 0.0916
-6.500 -0.5517 0.03648 0.02953 -0.0403 1.0000 0.0913
-6.250 -0.5374 0.03360 0.02618 -0.0388 1.0000 0.0941
-6.000 -0.5206 0.03084 0.02287 -0.0374 1.0000 0.0959
-5.750 -0.5015 0.02888 0.02029 -0.0360 1.0000 0.0980
-5.500 -0.4818 0.02675 0.01817 -0.0353 1.0000 0.1024
-5.250 -0.4602 0.02529 0.01651 -0.0342 1.0000 0.1058
-5.000 -0.4375 0.02387 0.01477 -0.0333 1.0000 0.1094
-4.750 -0.4146 0.02256 0.01329 -0.0325 1.0000 0.1149
-4.500 -0.3916 0.02158 0.01226 -0.0317 1.0000 0.1209
-4.250 -0.3673 0.02064 0.01109 -0.0309 1.0000 0.1272
-4.000 -0.3436 0.01960 0.01019 -0.0303 1.0000 0.1361
-3.750 -0.3197 0.01882 0.00947 -0.0298 1.0000 0.1508
-3.500 -0.2953 0.01802 0.00876 -0.0294 1.0000 0.1740
-3.250 -0.2709 0.01722 0.00821 -0.0290 1.0000 0.2105
-3.000 -0.2467 0.01657 0.00785 -0.0288 1.0000 0.2649
-2.750 -0.2228 0.01598 0.00764 -0.0286 1.0000 0.3339
-2.500 -0.1991 0.01536 0.00755 -0.0283 1.0000 0.4284
-2.250 -0.1771 0.01470 0.00763 -0.0274 1.0000 0.5734
-2.000 -0.1602 0.01420 0.00788 -0.0242 1.0000 0.7531
-1.750 -0.1292 0.01404 0.00804 -0.0237 1.0000 1.0000
-1.500 -0.1095 0.01428 0.00804 -0.0233 1.0000 1.0000
-1.250 -0.0755 0.01461 0.00815 -0.0257 0.9961 1.0000
-1.000 -0.0239 0.01498 0.00828 -0.0311 0.9866 1.0000
-0.750 0.0262 0.01528 0.00841 -0.0361 0.9763 1.0000
-0.500 0.0746 0.01551 0.00850 -0.0407 0.9651 1.0000
-0.250 0.1214 0.01569 0.00857 -0.0448 0.9532 1.0000
0.000 0.1682 0.01580 0.00860 -0.0488 0.9414 1.0000
0.250 0.2227 0.01581 0.00855 -0.0541 0.9325 1.0000
0.500 0.2669 0.01577 0.00848 -0.0573 0.9192 1.0000
0.750 0.3095 0.01569 0.00839 -0.0600 0.9060 1.0000
1.000 0.3504 0.01557 0.00826 -0.0621 0.8926 1.0000
1.250 0.3889 0.01541 0.00810 -0.0637 0.8787 1.0000
1.500 0.4245 0.01524 0.00794 -0.0645 0.8640 1.0000
1.750 0.4574 0.01509 0.00779 -0.0648 0.8484 1.0000
2.000 0.4880 0.01495 0.00767 -0.0645 0.8321 1.0000
2.250 0.5173 0.01484 0.00754 -0.0639 0.8153 1.0000
2.500 0.5455 0.01475 0.00744 -0.0631 0.7980 1.0000
2.750 0.5715 0.01476 0.00745 -0.0620 0.7789 1.0000
3.000 0.5966 0.01482 0.00750 -0.0608 0.7587 1.0000
3.250 0.6225 0.01486 0.00751 -0.0597 0.7390 1.0000
3.500 0.6487 0.01492 0.00754 -0.0586 0.7195 1.0000
3.750 0.6726 0.01509 0.00771 -0.0573 0.6967 1.0000
4.000 0.6980 0.01518 0.00774 -0.0560 0.6749 1.0000
4.250 0.7215 0.01535 0.00791 -0.0546 0.6496 1.0000
4.500 0.7457 0.01550 0.00802 -0.0532 0.6249 1.0000
4.750 0.7696 0.01569 0.00817 -0.0519 0.5994 1.0000
5.000 0.7922 0.01588 0.00834 -0.0504 0.5700 1.0000
5.250 0.8137 0.01604 0.00840 -0.0486 0.5353 1.0000
5.500 0.8342 0.01625 0.00855 -0.0468 0.4961 1.0000
5.750 0.8551 0.01655 0.00877 -0.0451 0.4588 1.0000
6.000 0.8752 0.01691 0.00911 -0.0435 0.4161 1.0000
6.250 0.8931 0.01743 0.00947 -0.0415 0.3588 1.0000
6.500 0.9062 0.01847 0.01005 -0.0391 0.2706 1.0000
6.750 0.9145 0.02041 0.01126 -0.0362 0.1828 1.0000
7.000 0.9267 0.02225 0.01267 -0.0339 0.1457 1.0000
7.250 0.9444 0.02374 0.01407 -0.0322 0.1279 1.0000
7.500 0.9643 0.02527 0.01545 -0.0309 0.1170 1.0000
7.750 0.9862 0.02654 0.01672 -0.0299 0.1080 1.0000
8.000 1.0105 0.02827 0.01845 -0.0293 0.1021 1.0000
8.250 1.0349 0.02982 0.02016 -0.0286 0.0970 1.0000
8.500 1.0609 0.03209 0.02226 -0.0287 0.0915 1.0000
8.750 1.0823 0.03371 0.02425 -0.0274 0.0879 1.0000
9.000 1.1038 0.03566 0.02646 -0.0264 0.0841 1.0000
9.250 1.1247 0.03768 0.02851 -0.0258 0.0798 1.0000
9.500 1.1418 0.04090 0.03203 -0.0246 0.0772 1.0000
9.750 1.1528 0.04335 0.03505 -0.0223 0.0749 1.0000
10.000 1.1622 0.04594 0.03805 -0.0202 0.0720 1.0000
10.250 1.1719 0.04876 0.04116 -0.0183 0.0698 1.0000
10.500 1.1830 0.05184 0.04442 -0.0169 0.0680 1.0000
10.750 1.1890 0.05631 0.04903 -0.0157 0.0661 1.0000
11.000 1.1804 0.06064 0.05376 -0.0129 0.0653 1.0000
11.250 1.1669 0.06407 0.05760 -0.0097 0.0649 1.0000
11.500 1.1497 0.06782 0.06167 -0.0067 0.0648 1.0000
11.750 1.1301 0.07183 0.06591 -0.0042 0.0650 1.0000
12.000 1.1111 0.07654 0.07080 -0.0029 0.0653 1.0000
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Polar data table (+)
Polar graphs
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