NACA 2412 (naca2412-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2412 (naca2412-il) Reynolds number: 100,000 Max Cl/Cd: 50.04 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2412-il-100000.txt Download as CSV file: xf-naca2412-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4676 0.09591 0.09056 -0.0237 1.0000 0.1755
-9.000 -0.6490 0.06371 0.05820 -0.0496 1.0000 0.1058
-8.750 -0.6415 0.05994 0.05441 -0.0485 1.0000 0.1028
-8.500 -0.6490 0.05536 0.04969 -0.0471 1.0000 0.1010
-8.250 -0.6597 0.05048 0.04453 -0.0453 1.0000 0.0998
-8.000 -0.6647 0.04615 0.03984 -0.0432 1.0000 0.0994
-7.750 -0.6640 0.04234 0.03564 -0.0410 1.0000 0.0995
-7.500 -0.6588 0.03888 0.03177 -0.0389 1.0000 0.0996
-7.250 -0.6495 0.03591 0.02836 -0.0369 1.0000 0.1001
-7.000 -0.6370 0.03353 0.02555 -0.0350 1.0000 0.1020
-6.750 -0.6223 0.03168 0.02319 -0.0332 1.0000 0.1043
-6.500 -0.6052 0.02943 0.02072 -0.0320 1.0000 0.1066
-6.250 -0.5859 0.02792 0.01913 -0.0308 1.0000 0.1094
-6.000 -0.5659 0.02665 0.01770 -0.0297 1.0000 0.1128
-5.750 -0.5454 0.02556 0.01633 -0.0285 1.0000 0.1179
-5.500 -0.5240 0.02425 0.01500 -0.0277 1.0000 0.1234
-5.250 -0.5023 0.02334 0.01401 -0.0267 1.0000 0.1303
-5.000 -0.4796 0.02227 0.01289 -0.0260 1.0000 0.1383
-4.750 -0.4571 0.02158 0.01212 -0.0253 1.0000 0.1505
-4.500 -0.4346 0.02090 0.01149 -0.0246 1.0000 0.1654
-4.250 -0.4122 0.02023 0.01097 -0.0241 1.0000 0.1829
-4.000 -0.3902 0.01975 0.01062 -0.0235 1.0000 0.2038
-3.750 -0.3680 0.01937 0.01030 -0.0229 1.0000 0.2293
-3.500 -0.3461 0.01903 0.01012 -0.0225 1.0000 0.2585
-3.250 -0.3240 0.01868 0.00996 -0.0221 1.0000 0.2943
-3.000 -0.3019 0.01831 0.00987 -0.0217 1.0000 0.3378
-2.750 -0.2753 0.01795 0.00982 -0.0222 0.9986 0.3943
-2.500 -0.2306 0.01757 0.00992 -0.0259 0.9915 0.4789
-2.250 -0.1869 0.01728 0.01014 -0.0291 0.9841 0.5825
-2.000 -0.1494 0.01704 0.01035 -0.0304 0.9748 0.6944
-1.750 -0.1161 0.01697 0.01065 -0.0302 0.9650 0.8044
-1.500 -0.0695 0.01716 0.01096 -0.0322 0.9578 0.9127
-1.250 0.0156 0.01742 0.01109 -0.0429 0.9534 0.9916
-1.000 0.0782 0.01739 0.01088 -0.0503 0.9458 1.0000
-0.750 0.1209 0.01732 0.01067 -0.0539 0.9330 1.0000
-0.500 0.1665 0.01724 0.01047 -0.0577 0.9215 1.0000
-0.250 0.2237 0.01701 0.01015 -0.0633 0.9139 1.0000
0.000 0.2623 0.01684 0.00991 -0.0654 0.9003 1.0000
0.250 0.3002 0.01665 0.00966 -0.0672 0.8869 1.0000
0.500 0.3370 0.01643 0.00939 -0.0685 0.8737 1.0000
0.750 0.3725 0.01619 0.00910 -0.0695 0.8606 1.0000
1.000 0.4063 0.01593 0.00881 -0.0699 0.8473 1.0000
1.250 0.4371 0.01571 0.00854 -0.0698 0.8332 1.0000
1.500 0.4637 0.01560 0.00838 -0.0689 0.8173 1.0000
1.750 0.4896 0.01553 0.00825 -0.0679 0.8011 1.0000
2.000 0.5150 0.01549 0.00816 -0.0668 0.7847 1.0000
2.250 0.5396 0.01550 0.00812 -0.0656 0.7678 1.0000
2.500 0.5637 0.01556 0.00813 -0.0643 0.7505 1.0000
2.750 0.5877 0.01565 0.00817 -0.0631 0.7331 1.0000
3.000 0.6117 0.01576 0.00823 -0.0618 0.7155 1.0000
3.250 0.6359 0.01588 0.00832 -0.0607 0.6979 1.0000
3.500 0.6601 0.01603 0.00843 -0.0595 0.6804 1.0000
3.750 0.6843 0.01620 0.00856 -0.0584 0.6628 1.0000
4.000 0.7087 0.01639 0.00871 -0.0573 0.6452 1.0000
4.250 0.7331 0.01659 0.00889 -0.0562 0.6275 1.0000
4.500 0.7575 0.01680 0.00906 -0.0551 0.6095 1.0000
4.750 0.7821 0.01697 0.00915 -0.0540 0.5902 1.0000
5.000 0.8043 0.01717 0.00935 -0.0525 0.5674 1.0000
5.250 0.8272 0.01736 0.00947 -0.0511 0.5447 1.0000
5.500 0.8503 0.01760 0.00963 -0.0498 0.5229 1.0000
5.750 0.8718 0.01787 0.00992 -0.0484 0.4990 1.0000
6.000 0.8941 0.01813 0.01008 -0.0470 0.4753 1.0000
6.250 0.9140 0.01840 0.01038 -0.0453 0.4478 1.0000
6.500 0.9336 0.01869 0.01064 -0.0436 0.4192 1.0000
6.750 0.9522 0.01903 0.01094 -0.0418 0.3879 1.0000
7.000 0.9695 0.01946 0.01129 -0.0398 0.3531 1.0000
7.250 0.9849 0.02006 0.01171 -0.0376 0.3145 1.0000
7.500 0.9979 0.02093 0.01235 -0.0352 0.2703 1.0000
7.750 1.0091 0.02212 0.01328 -0.0327 0.2267 1.0000
8.000 1.0201 0.02352 0.01435 -0.0302 0.1933 1.0000
8.250 1.0338 0.02486 0.01554 -0.0281 0.1685 1.0000
8.500 1.0496 0.02622 0.01676 -0.0264 0.1519 1.0000
8.750 1.0677 0.02760 0.01807 -0.0250 0.1395 1.0000
9.000 1.0874 0.02904 0.01944 -0.0240 0.1298 1.0000
9.250 1.1079 0.03035 0.02072 -0.0230 0.1217 1.0000
9.500 1.1314 0.03206 0.02248 -0.0225 0.1157 1.0000
9.750 1.1526 0.03349 0.02400 -0.0216 0.1100 1.0000
10.000 1.1784 0.03556 0.02597 -0.0217 0.1048 1.0000
10.250 1.1961 0.03723 0.02797 -0.0203 0.1011 1.0000
10.500 1.2140 0.03894 0.02985 -0.0192 0.0972 1.0000
10.750 1.2391 0.04137 0.03216 -0.0194 0.0930 1.0000
11.000 1.2486 0.04359 0.03478 -0.0172 0.0908 1.0000
11.250 1.2553 0.04577 0.03737 -0.0148 0.0882 1.0000
11.500 1.2639 0.04793 0.03977 -0.0128 0.0854 1.0000
11.750 1.2761 0.05012 0.04207 -0.0115 0.0828 1.0000
12.000 1.2907 0.05426 0.04622 -0.0112 0.0802 1.0000
12.250 1.2781 0.05664 0.04906 -0.0072 0.0793 1.0000
12.500 1.2610 0.05934 0.05213 -0.0031 0.0786 1.0000
12.750 1.2411 0.06248 0.05559 0.0004 0.0780 1.0000
13.000 1.2187 0.06618 0.05959 0.0029 0.0776 1.0000
13.250 1.1933 0.07055 0.06423 0.0044 0.0775 1.0000
13.500 1.1650 0.07573 0.06968 0.0045 0.0777 1.0000
13.750 1.1339 0.08190 0.07607 0.0032 0.0781 1.0000
14.000 1.1009 0.08918 0.08355 0.0004 0.0787 1.0000
14.250 1.0677 0.09758 0.09211 -0.0035 0.0794 1.0000
14.500 1.0377 0.10673 0.10136 -0.0080 0.0800 1.0000
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Polar data table (+)
Polar graphs
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