NACA 2415 (naca2415-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2415 (naca2415-il) Reynolds number: 100,000 Max Cl/Cd: 47.21 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2415-il-100000-n5.txt Download as CSV file: xf-naca2415-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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.8013 0.06679 0.06013 -0.0667 1.0000 0.0572
-13.250 -0.8380 0.05901 0.05206 -0.0716 1.0000 0.0573
-13.000 -0.8601 0.05413 0.04695 -0.0734 1.0000 0.0576
-12.750 -0.8769 0.05048 0.04308 -0.0734 1.0000 0.0581
-12.500 -0.8908 0.04758 0.03996 -0.0721 1.0000 0.0587
-12.250 -0.9034 0.04524 0.03740 -0.0695 1.0000 0.0593
-12.000 -0.9148 0.04327 0.03522 -0.0658 1.0000 0.0600
-11.750 -0.9209 0.04134 0.03302 -0.0625 1.0000 0.0607
-11.500 -0.9143 0.04002 0.03171 -0.0603 1.0000 0.0614
-11.250 -0.9078 0.03883 0.03050 -0.0579 1.0000 0.0623
-11.000 -0.9017 0.03769 0.02929 -0.0553 1.0000 0.0633
-10.750 -0.8954 0.03653 0.02804 -0.0527 1.0000 0.0646
-10.500 -0.8888 0.03532 0.02668 -0.0501 1.0000 0.0661
-10.250 -0.8813 0.03407 0.02522 -0.0474 1.0000 0.0677
-10.000 -0.8716 0.03297 0.02405 -0.0450 1.0000 0.0691
-9.750 -0.8606 0.03209 0.02318 -0.0428 1.0000 0.0706
-9.500 -0.8493 0.03119 0.02224 -0.0405 1.0000 0.0722
-9.250 -0.8375 0.03028 0.02123 -0.0382 1.0000 0.0742
-9.000 -0.8250 0.02937 0.02015 -0.0360 1.0000 0.0767
-8.750 -0.8123 0.02859 0.01940 -0.0340 1.0000 0.0789
-8.500 -0.7989 0.02790 0.01870 -0.0319 1.0000 0.0815
-8.250 -0.7845 0.02718 0.01788 -0.0300 1.0000 0.0848
-8.000 -0.7699 0.02647 0.01712 -0.0281 1.0000 0.0879
-7.750 -0.7395 0.02574 0.01638 -0.0294 0.9961 0.0927
-7.500 -0.7062 0.02500 0.01556 -0.0311 0.9916 0.0988
-7.250 -0.6737 0.02435 0.01489 -0.0327 0.9862 0.1056
-7.000 -0.6387 0.02371 0.01425 -0.0347 0.9818 0.1135
-6.750 -0.6073 0.02315 0.01362 -0.0358 0.9754 0.1226
-6.500 -0.5724 0.02260 0.01308 -0.0378 0.9703 0.1327
-6.250 -0.5413 0.02207 0.01258 -0.0388 0.9637 0.1432
-6.000 -0.5070 0.02157 0.01210 -0.0405 0.9579 0.1556
-5.750 -0.4734 0.02112 0.01164 -0.0420 0.9520 0.1690
-5.500 -0.4417 0.02069 0.01124 -0.0430 0.9447 0.1833
-5.250 -0.4041 0.02025 0.01084 -0.0452 0.9402 0.2000
-5.000 -0.3759 0.01989 0.01051 -0.0454 0.9314 0.2160
-4.750 -0.3404 0.01948 0.01017 -0.0471 0.9258 0.2349
-4.500 -0.3095 0.01912 0.00986 -0.0477 0.9183 0.2539
-4.250 -0.2780 0.01876 0.00955 -0.0485 0.9106 0.2740
-4.000 -0.2434 0.01838 0.00922 -0.0498 0.9048 0.2961
-3.750 -0.2164 0.01807 0.00897 -0.0495 0.8947 0.3168
-3.500 -0.1812 0.01768 0.00864 -0.0508 0.8890 0.3413
-3.250 -0.1559 0.01740 0.00845 -0.0502 0.8779 0.3639
-3.000 -0.1219 0.01701 0.00814 -0.0512 0.8715 0.3922
-2.750 -0.0968 0.01673 0.00799 -0.0505 0.8600 0.4196
-2.500 -0.0652 0.01638 0.00775 -0.0509 0.8521 0.4536
-2.250 -0.0389 0.01611 0.00763 -0.0503 0.8407 0.4894
-2.000 -0.0105 0.01584 0.00749 -0.0500 0.8307 0.5289
-1.750 0.0182 0.01558 0.00735 -0.0497 0.8204 0.5695
-1.500 0.0448 0.01540 0.00728 -0.0489 0.8085 0.6088
-1.250 0.0746 0.01517 0.00715 -0.0486 0.7986 0.6488
-1.000 0.1010 0.01504 0.00712 -0.0477 0.7857 0.6865
-0.750 0.1286 0.01494 0.00710 -0.0470 0.7735 0.7232
-0.500 0.1585 0.01484 0.00704 -0.0466 0.7624 0.7583
-0.250 0.1857 0.01483 0.00708 -0.0457 0.7490 0.7913
0.000 0.2150 0.01485 0.00711 -0.0453 0.7360 0.8215
0.250 0.2461 0.01487 0.00710 -0.0452 0.7239 0.8496
0.500 0.2789 0.01492 0.00713 -0.0456 0.7108 0.8744
0.750 0.3122 0.01501 0.00718 -0.0462 0.6971 0.8973
1.000 0.3477 0.01510 0.00720 -0.0473 0.6840 0.9180
1.250 0.3854 0.01519 0.00720 -0.0489 0.6711 0.9365
1.500 0.4242 0.01531 0.00726 -0.0508 0.6571 0.9535
1.750 0.4671 0.01543 0.00733 -0.0537 0.6428 0.9683
2.000 0.5130 0.01554 0.00737 -0.0573 0.6285 0.9817
2.250 0.5598 0.01562 0.00736 -0.0612 0.6127 0.9941
2.500 0.5936 0.01570 0.00735 -0.0626 0.5965 1.0000
2.750 0.6138 0.01581 0.00734 -0.0612 0.5820 1.0000
3.000 0.6335 0.01594 0.00744 -0.0597 0.5676 1.0000
3.250 0.6538 0.01610 0.00755 -0.0584 0.5548 1.0000
3.500 0.6747 0.01628 0.00765 -0.0570 0.5429 1.0000
3.750 0.6954 0.01647 0.00780 -0.0557 0.5306 1.0000
4.000 0.7160 0.01668 0.00799 -0.0544 0.5182 1.0000
4.250 0.7371 0.01691 0.00815 -0.0530 0.5066 1.0000
4.500 0.7579 0.01714 0.00836 -0.0517 0.4944 1.0000
4.750 0.7784 0.01739 0.00859 -0.0503 0.4816 1.0000
5.000 0.7989 0.01765 0.00881 -0.0489 0.4687 1.0000
5.250 0.8191 0.01792 0.00902 -0.0474 0.4547 1.0000
5.500 0.8388 0.01819 0.00926 -0.0458 0.4397 1.0000
5.750 0.8585 0.01848 0.00954 -0.0443 0.4245 1.0000
6.000 0.8784 0.01879 0.00985 -0.0428 0.4099 1.0000
6.250 0.8983 0.01912 0.01016 -0.0414 0.3956 1.0000
6.500 0.9179 0.01948 0.01048 -0.0399 0.3811 1.0000
6.750 0.9371 0.01985 0.01082 -0.0384 0.3662 1.0000
7.000 0.9557 0.02026 0.01120 -0.0368 0.3505 1.0000
7.250 0.9736 0.02069 0.01161 -0.0351 0.3340 1.0000
7.500 0.9909 0.02115 0.01204 -0.0334 0.3168 1.0000
7.750 1.0073 0.02166 0.01252 -0.0316 0.2990 1.0000
8.000 1.0231 0.02219 0.01304 -0.0297 0.2804 1.0000
8.250 1.0379 0.02278 0.01359 -0.0278 0.2618 1.0000
8.500 1.0515 0.02344 0.01419 -0.0257 0.2438 1.0000
8.750 1.0638 0.02416 0.01486 -0.0235 0.2272 1.0000
9.000 1.0740 0.02493 0.01557 -0.0210 0.2121 1.0000
9.250 1.0834 0.02576 0.01636 -0.0184 0.1982 1.0000
9.500 1.0924 0.02668 0.01724 -0.0160 0.1849 1.0000
9.750 1.1018 0.02764 0.01820 -0.0138 0.1719 1.0000
10.000 1.1113 0.02865 0.01922 -0.0118 0.1597 1.0000
10.250 1.1198 0.02976 0.02033 -0.0097 0.1488 1.0000
10.500 1.1268 0.03101 0.02157 -0.0078 0.1395 1.0000
10.750 1.1335 0.03235 0.02291 -0.0059 0.1309 1.0000
11.000 1.1402 0.03375 0.02435 -0.0042 0.1233 1.0000
11.250 1.1446 0.03537 0.02597 -0.0026 0.1169 1.0000
11.500 1.1509 0.03695 0.02761 -0.0012 0.1108 1.0000
11.750 1.1548 0.03875 0.02943 0.0001 0.1056 1.0000
12.000 1.1590 0.04062 0.03134 0.0013 0.1010 1.0000
12.250 1.1639 0.04250 0.03331 0.0023 0.0964 1.0000
12.500 1.1660 0.04465 0.03547 0.0032 0.0930 1.0000
12.750 1.1706 0.04669 0.03759 0.0040 0.0895 1.0000
13.000 1.1749 0.04880 0.03979 0.0046 0.0863 1.0000
13.250 1.1779 0.05107 0.04210 0.0051 0.0837 1.0000
13.500 1.1806 0.05337 0.04441 0.0056 0.0815 1.0000
13.750 1.1849 0.05566 0.04685 0.0060 0.0789 1.0000
14.000 1.1882 0.05806 0.04935 0.0063 0.0766 1.0000
14.250 1.1908 0.06053 0.05188 0.0064 0.0746 1.0000
14.500 1.1939 0.06296 0.05431 0.0066 0.0730 1.0000
14.750 1.1973 0.06550 0.05697 0.0067 0.0714 1.0000
15.000 1.1996 0.06825 0.05989 0.0066 0.0698 1.0000
15.250 1.2012 0.07109 0.06285 0.0064 0.0683 1.0000
15.500 1.2027 0.07396 0.06581 0.0061 0.0669 1.0000
15.750 1.2049 0.07674 0.06863 0.0058 0.0656 1.0000
16.000 1.2098 0.07912 0.07100 0.0057 0.0645 1.0000
16.250 1.2060 0.08296 0.07504 0.0048 0.0634 1.0000
16.500 1.2004 0.08716 0.07946 0.0035 0.0623 1.0000
16.750 1.1943 0.09150 0.08400 0.0021 0.0613 1.0000
17.000 1.1876 0.09603 0.08869 0.0005 0.0605 1.0000
17.250 1.1801 0.10076 0.09358 -0.0014 0.0596 1.0000
17.500 1.1731 0.10548 0.09843 -0.0033 0.0588 1.0000
17.750 1.1689 0.10975 0.10280 -0.0052 0.0580 1.0000
18.000 1.1726 0.11258 0.10563 -0.0061 0.0571 1.0000
18.250 1.1580 0.11899 0.11222 -0.0094 0.0565 1.0000
18.500 1.1204 0.13042 0.12398 -0.0164 0.0562 1.0000
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