NACA 2415 (n2415-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2415 (n2415-il) Reynolds number: 100,000 Max Cl/Cd: 47.22 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n2415-il-100000-n5.txt Download as CSV file: xf-n2415-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7843 0.07237 0.06585 -0.0624 1.0000 0.0553
-13.500 -0.8315 0.06207 0.05522 -0.0696 1.0000 0.0552
-13.250 -0.8573 0.05616 0.04906 -0.0727 1.0000 0.0555
-13.000 -0.8765 0.05181 0.04447 -0.0738 1.0000 0.0561
-12.750 -0.8925 0.04836 0.04076 -0.0734 1.0000 0.0568
-12.500 -0.9069 0.04555 0.03769 -0.0716 1.0000 0.0575
-12.250 -0.9154 0.04353 0.03549 -0.0688 1.0000 0.0583
-12.000 -0.9134 0.04235 0.03434 -0.0663 1.0000 0.0592
-11.750 -0.9122 0.04114 0.03310 -0.0635 1.0000 0.0602
-11.500 -0.9110 0.03986 0.03171 -0.0607 1.0000 0.0615
-11.250 -0.9095 0.03845 0.03015 -0.0577 1.0000 0.0629
-11.000 -0.9077 0.03695 0.02840 -0.0547 1.0000 0.0646
-10.750 -0.9009 0.03575 0.02714 -0.0521 1.0000 0.0659
-10.500 -0.8920 0.03485 0.02625 -0.0497 1.0000 0.0674
-10.250 -0.8835 0.03388 0.02521 -0.0472 1.0000 0.0693
-10.000 -0.8748 0.03281 0.02397 -0.0446 1.0000 0.0715
-9.750 -0.8648 0.03175 0.02277 -0.0422 1.0000 0.0736
-9.500 -0.8533 0.03096 0.02201 -0.0400 1.0000 0.0755
-9.250 -0.8415 0.03016 0.02116 -0.0378 1.0000 0.0780
-9.000 -0.8289 0.02930 0.02013 -0.0356 1.0000 0.0810
-8.750 -0.8158 0.02851 0.01932 -0.0335 1.0000 0.0835
-8.500 -0.8021 0.02784 0.01864 -0.0315 1.0000 0.0863
-8.250 -0.7874 0.02715 0.01784 -0.0296 1.0000 0.0900
-8.000 -0.7725 0.02647 0.01713 -0.0278 1.0000 0.0934
-7.750 -0.7409 0.02576 0.01640 -0.0293 0.9959 0.0985
-7.500 -0.7077 0.02504 0.01561 -0.0310 0.9914 0.1044
-7.250 -0.6749 0.02441 0.01494 -0.0325 0.9862 0.1109
-7.000 -0.6399 0.02378 0.01431 -0.0345 0.9819 0.1182
-6.750 -0.6086 0.02323 0.01366 -0.0356 0.9755 0.1265
-6.500 -0.5740 0.02266 0.01315 -0.0375 0.9704 0.1354
-6.250 -0.5427 0.02213 0.01263 -0.0386 0.9640 0.1451
-6.000 -0.5086 0.02165 0.01212 -0.0401 0.9580 0.1567
-5.750 -0.4734 0.02118 0.01165 -0.0419 0.9527 0.1697
-5.500 -0.4430 0.02073 0.01125 -0.0427 0.9449 0.1827
-5.250 -0.4053 0.02027 0.01084 -0.0448 0.9401 0.1987
-5.000 -0.3763 0.01988 0.01049 -0.0452 0.9315 0.2143
-4.750 -0.3406 0.01947 0.01012 -0.0469 0.9255 0.2330
-4.500 -0.3087 0.01910 0.00979 -0.0478 0.9183 0.2521
-4.250 -0.2777 0.01875 0.00947 -0.0484 0.9103 0.2724
-4.000 -0.2414 0.01832 0.00915 -0.0500 0.9053 0.2950
-3.750 -0.2164 0.01803 0.00893 -0.0494 0.8944 0.3161
-3.500 -0.1816 0.01765 0.00861 -0.0507 0.8884 0.3421
-3.250 -0.1561 0.01737 0.00842 -0.0501 0.8776 0.3663
-3.000 -0.1229 0.01698 0.00813 -0.0509 0.8708 0.3952
-2.750 -0.0974 0.01672 0.00798 -0.0503 0.8595 0.4239
-2.500 -0.0649 0.01636 0.00774 -0.0508 0.8523 0.4588
-2.250 -0.0401 0.01612 0.00764 -0.0500 0.8402 0.4932
-2.000 -0.0101 0.01582 0.00747 -0.0499 0.8314 0.5320
-1.750 0.0166 0.01560 0.00737 -0.0493 0.8197 0.5705
-1.500 0.0440 0.01540 0.00728 -0.0487 0.8087 0.6099
-1.250 0.0734 0.01519 0.00717 -0.0483 0.7985 0.6494
-1.000 0.0996 0.01507 0.00715 -0.0474 0.7856 0.6869
-0.750 0.1284 0.01495 0.00711 -0.0469 0.7744 0.7240
-0.500 0.1572 0.01486 0.00707 -0.0463 0.7624 0.7592
-0.250 0.1849 0.01485 0.00711 -0.0455 0.7492 0.7923
0.000 0.2145 0.01484 0.00711 -0.0451 0.7369 0.8242
0.250 0.2475 0.01487 0.00711 -0.0453 0.7246 0.8519
0.500 0.2792 0.01495 0.00717 -0.0455 0.7105 0.8781
0.750 0.3133 0.01503 0.00720 -0.0462 0.6969 0.9013
1.000 0.3507 0.01512 0.00721 -0.0476 0.6837 0.9211
1.250 0.3886 0.01522 0.00723 -0.0493 0.6699 0.9390
1.500 0.4274 0.01534 0.00728 -0.0513 0.6552 0.9551
1.750 0.4690 0.01545 0.00732 -0.0539 0.6406 0.9689
2.000 0.5125 0.01555 0.00734 -0.0570 0.6263 0.9814
2.250 0.5582 0.01564 0.00734 -0.0607 0.6118 0.9932
2.500 0.5949 0.01572 0.00736 -0.0627 0.5973 1.0000
2.750 0.6148 0.01584 0.00743 -0.0613 0.5841 1.0000
3.000 0.6354 0.01598 0.00750 -0.0600 0.5717 1.0000
3.250 0.6562 0.01613 0.00756 -0.0587 0.5594 1.0000
3.500 0.6762 0.01631 0.00771 -0.0573 0.5462 1.0000
3.750 0.6968 0.01649 0.00786 -0.0559 0.5336 1.0000
4.000 0.7179 0.01670 0.00797 -0.0545 0.5214 1.0000
4.250 0.7380 0.01691 0.00817 -0.0531 0.5081 1.0000
4.500 0.7585 0.01714 0.00838 -0.0517 0.4951 1.0000
4.750 0.7791 0.01739 0.00857 -0.0503 0.4824 1.0000
5.000 0.7994 0.01764 0.00878 -0.0488 0.4692 1.0000
5.250 0.8193 0.01791 0.00905 -0.0473 0.4551 1.0000
5.500 0.8394 0.01819 0.00931 -0.0458 0.4410 1.0000
5.750 0.8593 0.01848 0.00956 -0.0443 0.4267 1.0000
6.000 0.8790 0.01879 0.00983 -0.0428 0.4120 1.0000
6.250 0.8985 0.01912 0.01013 -0.0412 0.3968 1.0000
6.500 0.9176 0.01946 0.01047 -0.0397 0.3809 1.0000
6.750 0.9364 0.01983 0.01082 -0.0381 0.3648 1.0000
7.000 0.9548 0.02022 0.01120 -0.0365 0.3482 1.0000
7.250 0.9727 0.02066 0.01161 -0.0348 0.3314 1.0000
7.500 0.9899 0.02113 0.01204 -0.0330 0.3144 1.0000
7.750 1.0064 0.02164 0.01252 -0.0312 0.2973 1.0000
8.000 1.0221 0.02220 0.01304 -0.0294 0.2803 1.0000
8.250 1.0370 0.02280 0.01360 -0.0274 0.2635 1.0000
8.500 1.0510 0.02345 0.01421 -0.0254 0.2471 1.0000
8.750 1.0641 0.02415 0.01488 -0.0232 0.2313 1.0000
9.000 1.0753 0.02488 0.01558 -0.0209 0.2166 1.0000
9.250 1.0855 0.02567 0.01635 -0.0184 0.2029 1.0000
9.500 1.0951 0.02654 0.01719 -0.0160 0.1901 1.0000
9.750 1.1039 0.02751 0.01813 -0.0137 0.1783 1.0000
10.000 1.1125 0.02854 0.01915 -0.0115 0.1672 1.0000
10.250 1.1218 0.02961 0.02024 -0.0095 0.1566 1.0000
10.500 1.1296 0.03080 0.02144 -0.0076 0.1476 1.0000
10.750 1.1363 0.03211 0.02275 -0.0057 0.1393 1.0000
11.000 1.1444 0.03342 0.02411 -0.0041 0.1314 1.0000
11.250 1.1489 0.03499 0.02565 -0.0024 0.1251 1.0000
11.500 1.1567 0.03644 0.02719 -0.0010 0.1182 1.0000
11.750 1.1603 0.03821 0.02895 0.0004 0.1130 1.0000
12.000 1.1670 0.03986 0.03071 0.0015 0.1075 1.0000
12.250 1.1707 0.04177 0.03265 0.0026 0.1029 1.0000
12.500 1.1748 0.04374 0.03467 0.0035 0.0988 1.0000
12.750 1.1793 0.04575 0.03677 0.0043 0.0946 1.0000
13.000 1.1814 0.04798 0.03901 0.0050 0.0913 1.0000
13.250 1.1851 0.05019 0.04132 0.0056 0.0878 1.0000
13.500 1.1881 0.05250 0.04373 0.0060 0.0845 1.0000
13.750 1.1897 0.05496 0.04623 0.0063 0.0819 1.0000
14.000 1.1919 0.05744 0.04877 0.0066 0.0794 1.0000
14.250 1.1939 0.06005 0.05152 0.0067 0.0766 1.0000
14.500 1.1948 0.06278 0.05433 0.0066 0.0743 1.0000
14.750 1.1959 0.06549 0.05706 0.0065 0.0724 1.0000
15.000 1.1966 0.06842 0.06012 0.0063 0.0703 1.0000
15.250 1.1962 0.07158 0.06343 0.0059 0.0683 1.0000
15.500 1.1956 0.07475 0.06670 0.0054 0.0664 1.0000
15.750 1.1959 0.07779 0.06978 0.0049 0.0648 1.0000
16.000 1.1958 0.08097 0.07302 0.0043 0.0633 1.0000
16.250 1.1904 0.08513 0.07740 0.0031 0.0618 1.0000
16.500 1.1855 0.08926 0.08169 0.0018 0.0604 1.0000
16.750 1.1816 0.09326 0.08581 0.0005 0.0590 1.0000
17.000 1.1803 0.09685 0.08945 -0.0007 0.0578 1.0000
17.250 1.1827 0.09975 0.09233 -0.0015 0.0566 1.0000
17.500 1.1675 0.10603 0.09890 -0.0044 0.0556 1.0000
17.750 1.1513 0.11268 0.10579 -0.0077 0.0547 1.0000
18.000 1.1336 0.11984 0.11317 -0.0114 0.0538 1.0000
18.250 1.1124 0.12800 0.12154 -0.0160 0.0531 1.0000
18.500 1.0796 0.13909 0.13288 -0.0227 0.0525 1.0000
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Polar data table (+)
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