NACA 2415 (naca2415-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2415 (naca2415-il) Reynolds number: 200,000 Max Cl/Cd: 64.06 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2415-il-200000.txt Download as CSV file: xf-naca2415-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7945 0.07738 0.07278 -0.0629 1.0000 0.0605
-14.000 -0.8410 0.06704 0.06224 -0.0702 1.0000 0.0600
-13.750 -0.8790 0.05958 0.05453 -0.0747 1.0000 0.0598
-13.500 -0.9100 0.05420 0.04891 -0.0765 1.0000 0.0597
-13.250 -0.9359 0.05027 0.04473 -0.0758 1.0000 0.0598
-13.000 -0.9587 0.04737 0.04160 -0.0730 1.0000 0.0599
-12.750 -0.9793 0.04516 0.03918 -0.0685 1.0000 0.0601
-12.500 -0.9935 0.04304 0.03679 -0.0644 1.0000 0.0604
-12.250 -1.0033 0.04117 0.03464 -0.0602 1.0000 0.0607
-12.000 -0.9989 0.03881 0.03220 -0.0580 1.0000 0.0614
-11.750 -0.9889 0.03747 0.03087 -0.0559 1.0000 0.0623
-11.500 -0.9814 0.03633 0.02968 -0.0533 1.0000 0.0632
-11.250 -0.9739 0.03517 0.02842 -0.0507 1.0000 0.0641
-11.000 -0.9667 0.03391 0.02703 -0.0479 1.0000 0.0651
-10.750 -0.9594 0.03260 0.02554 -0.0451 1.0000 0.0660
-10.500 -0.9512 0.03133 0.02407 -0.0423 1.0000 0.0670
-10.250 -0.9421 0.03021 0.02272 -0.0396 1.0000 0.0680
-10.000 -0.9299 0.02883 0.02123 -0.0374 1.0000 0.0692
-9.750 -0.9147 0.02787 0.02033 -0.0357 1.0000 0.0706
-9.500 -0.9003 0.02712 0.01955 -0.0337 1.0000 0.0721
-9.250 -0.8859 0.02634 0.01868 -0.0317 1.0000 0.0738
-9.000 -0.8710 0.02554 0.01775 -0.0298 1.0000 0.0755
-8.750 -0.8557 0.02484 0.01687 -0.0278 1.0000 0.0771
-8.500 -0.8390 0.02379 0.01591 -0.0264 1.0000 0.0793
-8.250 -0.8220 0.02324 0.01539 -0.0248 1.0000 0.0817
-8.000 -0.8047 0.02273 0.01480 -0.0233 1.0000 0.0848
-7.750 -0.7830 0.02197 0.01400 -0.0226 0.9993 0.0882
-7.500 -0.7448 0.02134 0.01342 -0.0252 0.9954 0.0932
-7.250 -0.7070 0.02061 0.01266 -0.0276 0.9916 0.0996
-7.000 -0.6698 0.02012 0.01217 -0.0299 0.9866 0.1074
-6.750 -0.6306 0.01950 0.01162 -0.0326 0.9827 0.1167
-6.500 -0.5958 0.01893 0.01108 -0.0344 0.9772 0.1269
-6.250 -0.5577 0.01845 0.01061 -0.0367 0.9722 0.1390
-6.000 -0.5160 0.01802 0.01021 -0.0398 0.9690 0.1529
-5.750 -0.4847 0.01766 0.00985 -0.0407 0.9613 0.1658
-5.500 -0.4447 0.01722 0.00948 -0.0433 0.9572 0.1818
-5.250 -0.4085 0.01682 0.00916 -0.0452 0.9517 0.1986
-5.000 -0.3739 0.01642 0.00885 -0.0467 0.9451 0.2167
-4.750 -0.3320 0.01599 0.00854 -0.0496 0.9415 0.2385
-4.500 -0.2964 0.01563 0.00827 -0.0512 0.9355 0.2607
-4.250 -0.2604 0.01528 0.00796 -0.0528 0.9290 0.2850
-4.000 -0.2204 0.01479 0.00762 -0.0552 0.9251 0.3108
-3.750 -0.1895 0.01445 0.00736 -0.0557 0.9172 0.3356
-3.500 -0.1555 0.01402 0.00703 -0.0567 0.9105 0.3619
-3.250 -0.1182 0.01354 0.00667 -0.0583 0.9062 0.3915
-3.000 -0.0936 0.01322 0.00647 -0.0574 0.8948 0.4188
-2.750 -0.0597 0.01275 0.00614 -0.0582 0.8891 0.4542
-2.500 -0.0356 0.01244 0.00598 -0.0571 0.8772 0.4905
-2.250 -0.0065 0.01206 0.00577 -0.0568 0.8688 0.5335
-2.000 0.0195 0.01177 0.00562 -0.0559 0.8575 0.5772
-1.750 0.0454 0.01153 0.00551 -0.0550 0.8463 0.6198
-1.500 0.0734 0.01126 0.00534 -0.0543 0.8366 0.6603
-1.250 0.0979 0.01111 0.00530 -0.0531 0.8233 0.6982
-1.000 0.1238 0.01097 0.00525 -0.0520 0.8112 0.7349
-0.750 0.1508 0.01085 0.00518 -0.0510 0.8000 0.7700
-0.500 0.1753 0.01082 0.00524 -0.0496 0.7860 0.8030
-0.250 0.2009 0.01083 0.00529 -0.0483 0.7729 0.8343
0.000 0.2274 0.01087 0.00530 -0.0472 0.7604 0.8639
0.250 0.2557 0.01095 0.00535 -0.0464 0.7468 0.8884
0.500 0.2862 0.01107 0.00544 -0.0462 0.7326 0.9097
0.750 0.3205 0.01122 0.00552 -0.0469 0.7190 0.9279
1.000 0.3583 0.01137 0.00557 -0.0484 0.7052 0.9429
1.250 0.3985 0.01152 0.00561 -0.0505 0.6909 0.9559
1.500 0.4428 0.01166 0.00566 -0.0536 0.6745 0.9664
1.750 0.4897 0.01176 0.00566 -0.0574 0.6566 0.9749
2.000 0.5352 0.01186 0.00566 -0.0609 0.6393 0.9845
2.250 0.5828 0.01196 0.00569 -0.0650 0.6231 0.9937
2.500 0.6263 0.01203 0.00568 -0.0685 0.6074 1.0000
2.750 0.6477 0.01210 0.00567 -0.0675 0.5943 1.0000
3.250 0.6898 0.01231 0.00575 -0.0652 0.5685 1.0000
3.500 0.7108 0.01245 0.00585 -0.0639 0.5557 1.0000
3.750 0.7320 0.01262 0.00592 -0.0627 0.5436 1.0000
4.000 0.7525 0.01277 0.00602 -0.0613 0.5301 1.0000
4.250 0.7725 0.01292 0.00615 -0.0598 0.5156 1.0000
4.500 0.7927 0.01310 0.00628 -0.0583 0.5015 1.0000
4.750 0.8133 0.01331 0.00641 -0.0569 0.4888 1.0000
5.000 0.8338 0.01350 0.00657 -0.0555 0.4759 1.0000
5.250 0.8541 0.01370 0.00676 -0.0540 0.4626 1.0000
5.500 0.8745 0.01392 0.00695 -0.0525 0.4495 1.0000
5.750 0.8948 0.01417 0.00713 -0.0510 0.4364 1.0000
6.000 0.9146 0.01441 0.00734 -0.0494 0.4222 1.0000
6.250 0.9341 0.01464 0.00756 -0.0478 0.4069 1.0000
6.500 0.9534 0.01490 0.00779 -0.0462 0.3909 1.0000
6.750 0.9724 0.01518 0.00804 -0.0445 0.3740 1.0000
7.000 0.9910 0.01549 0.00830 -0.0428 0.3563 1.0000
7.250 1.0093 0.01584 0.00859 -0.0411 0.3382 1.0000
7.500 1.0272 0.01622 0.00892 -0.0393 0.3198 1.0000
7.750 1.0447 0.01664 0.00928 -0.0376 0.3013 1.0000
8.000 1.0614 0.01710 0.00967 -0.0357 0.2827 1.0000
8.250 1.0781 0.01757 0.01011 -0.0339 0.2635 1.0000
8.500 1.0936 0.01812 0.01060 -0.0319 0.2446 1.0000
8.750 1.1076 0.01874 0.01115 -0.0298 0.2267 1.0000
9.000 1.1200 0.01943 0.01176 -0.0274 0.2099 1.0000
9.250 1.1306 0.02015 0.01243 -0.0248 0.1941 1.0000
9.500 1.1411 0.02092 0.01315 -0.0222 0.1789 1.0000
9.750 1.1513 0.02176 0.01394 -0.0198 0.1644 1.0000
10.000 1.1608 0.02269 0.01482 -0.0174 0.1511 1.0000
10.250 1.1689 0.02376 0.01582 -0.0150 0.1395 1.0000
10.500 1.1756 0.02496 0.01695 -0.0127 0.1293 1.0000
10.750 1.1849 0.02609 0.01810 -0.0107 0.1199 1.0000
11.000 1.1912 0.02747 0.01945 -0.0086 0.1124 1.0000
11.250 1.1985 0.02882 0.02079 -0.0067 0.1058 1.0000
11.500 1.2056 0.03028 0.02226 -0.0050 0.1003 1.0000
11.750 1.2141 0.03166 0.02368 -0.0035 0.0956 1.0000
12.000 1.2200 0.03336 0.02529 -0.0018 0.0918 1.0000
12.250 1.2301 0.03472 0.02678 -0.0006 0.0884 1.0000
12.500 1.2390 0.03619 0.02828 0.0005 0.0853 1.0000
12.750 1.2477 0.03778 0.02980 0.0017 0.0826 1.0000
13.000 1.2574 0.03932 0.03143 0.0028 0.0802 1.0000
13.250 1.2667 0.04087 0.03309 0.0038 0.0779 1.0000
13.500 1.2765 0.04241 0.03467 0.0047 0.0760 1.0000
13.750 1.2872 0.04392 0.03615 0.0055 0.0742 1.0000
14.000 1.3024 0.04532 0.03751 0.0065 0.0723 1.0000
14.250 1.3083 0.04721 0.03958 0.0073 0.0710 1.0000
14.500 1.3149 0.04911 0.04161 0.0080 0.0695 1.0000
14.750 1.3221 0.05098 0.04358 0.0087 0.0681 1.0000
15.000 1.3308 0.05276 0.04541 0.0093 0.0669 1.0000
15.250 1.3426 0.05431 0.04696 0.0099 0.0656 1.0000
15.500 1.3593 0.05587 0.04850 0.0107 0.0641 1.0000
15.750 1.3569 0.05859 0.05143 0.0111 0.0634 1.0000
16.000 1.3552 0.06140 0.05444 0.0113 0.0625 1.0000
16.250 1.3540 0.06427 0.05749 0.0114 0.0616 1.0000
16.500 1.3526 0.06724 0.06061 0.0114 0.0607 1.0000
16.750 1.3506 0.07031 0.06383 0.0111 0.0599 1.0000
17.000 1.3508 0.07319 0.06681 0.0109 0.0590 1.0000
17.250 1.3556 0.07559 0.06924 0.0108 0.0581 1.0000
17.500 1.3721 0.07707 0.07065 0.0117 0.0569 1.0000
17.750 1.3558 0.08193 0.07576 0.0103 0.0565 1.0000
18.000 1.3365 0.08746 0.08156 0.0084 0.0562 1.0000
18.250 1.3152 0.09363 0.08799 0.0058 0.0559 1.0000
18.500 1.2904 0.10066 0.09529 0.0025 0.0557 1.0000
18.750 1.2610 0.10888 0.10377 -0.0019 0.0555 1.0000
19.000 1.2235 0.11911 0.11430 -0.0079 0.0555 1.0000
19.250 1.1678 0.13376 0.12928 -0.0172 0.0559 1.0000
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Polar data table (+)
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