NACA 2415 (n2415-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2415 (n2415-il) Reynolds number: 200,000 Max Cl/Cd: 61.5 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n2415-il-200000-n5.txt Download as CSV file: xf-n2415-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8683 0.09939 0.09441 -0.0426 1.0000 0.0351
-16.500 -0.9096 0.08798 0.08275 -0.0497 1.0000 0.0352
-16.250 -0.9378 0.07944 0.07399 -0.0549 1.0000 0.0354
-16.000 -0.9597 0.07230 0.06664 -0.0593 1.0000 0.0356
-15.750 -0.9755 0.06635 0.06051 -0.0629 1.0000 0.0359
-15.500 -0.9814 0.06219 0.05628 -0.0651 1.0000 0.0362
-15.250 -0.9869 0.05813 0.05214 -0.0674 1.0000 0.0365
-15.000 -0.9917 0.05426 0.04818 -0.0694 1.0000 0.0369
-14.750 -0.9955 0.05065 0.04446 -0.0713 1.0000 0.0373
-14.500 -0.9984 0.04733 0.04102 -0.0727 1.0000 0.0378
-14.250 -1.0002 0.04432 0.03789 -0.0738 1.0000 0.0383
-14.000 -1.0010 0.04162 0.03506 -0.0744 1.0000 0.0389
-13.750 -1.0009 0.03924 0.03252 -0.0745 1.0000 0.0396
-13.500 -1.0000 0.03713 0.03023 -0.0741 1.0000 0.0404
-13.250 -0.9979 0.03538 0.02841 -0.0731 1.0000 0.0410
-13.000 -0.9951 0.03392 0.02692 -0.0717 1.0000 0.0416
-12.750 -0.9925 0.03267 0.02561 -0.0697 1.0000 0.0423
-12.500 -0.9913 0.03159 0.02446 -0.0670 1.0000 0.0431
-12.250 -0.9922 0.03066 0.02346 -0.0634 1.0000 0.0439
-12.000 -0.9917 0.02979 0.02249 -0.0597 1.0000 0.0447
-11.750 -0.9871 0.02892 0.02150 -0.0566 1.0000 0.0456
-11.500 -0.9828 0.02810 0.02066 -0.0534 1.0000 0.0465
-11.250 -0.9766 0.02739 0.01992 -0.0503 1.0000 0.0474
-11.000 -0.9689 0.02672 0.01921 -0.0474 1.0000 0.0486
-10.750 -0.9601 0.02606 0.01847 -0.0446 1.0000 0.0499
-10.500 -0.9500 0.02541 0.01772 -0.0419 1.0000 0.0513
-10.250 -0.9403 0.02474 0.01703 -0.0393 1.0000 0.0525
-10.000 -0.9198 0.02406 0.01633 -0.0387 0.9984 0.0542
-9.750 -0.8894 0.02336 0.01554 -0.0399 0.9953 0.0566
-9.500 -0.8592 0.02263 0.01475 -0.0411 0.9922 0.0590
-9.250 -0.8299 0.02198 0.01408 -0.0421 0.9882 0.0615
-9.000 -0.7983 0.02139 0.01339 -0.0433 0.9847 0.0646
-8.750 -0.7659 0.02074 0.01275 -0.0449 0.9819 0.0677
-8.500 -0.7375 0.02020 0.01216 -0.0454 0.9768 0.0711
-8.250 -0.7061 0.01963 0.01157 -0.0465 0.9727 0.0748
-8.000 -0.6721 0.01911 0.01102 -0.0482 0.9698 0.0793
-7.750 -0.6431 0.01861 0.01050 -0.0487 0.9645 0.0836
-7.500 -0.6115 0.01814 0.01001 -0.0498 0.9598 0.0889
-7.250 -0.5770 0.01764 0.00952 -0.0514 0.9565 0.0947
-7.000 -0.5457 0.01723 0.00907 -0.0523 0.9517 0.1012
-6.750 -0.5170 0.01678 0.00866 -0.0526 0.9453 0.1079
-6.500 -0.4835 0.01637 0.00823 -0.0539 0.9409 0.1159
-6.250 -0.4548 0.01599 0.00786 -0.0542 0.9341 0.1246
-6.000 -0.4252 0.01559 0.00750 -0.0546 0.9272 0.1340
-5.750 -0.3920 0.01520 0.00712 -0.0557 0.9226 0.1449
-5.500 -0.3667 0.01492 0.00684 -0.0551 0.9131 0.1556
-5.250 -0.3358 0.01456 0.00651 -0.0557 0.9070 0.1685
-5.000 -0.3090 0.01425 0.00626 -0.0555 0.8983 0.1813
-4.750 -0.2796 0.01394 0.00598 -0.0557 0.8906 0.1956
-4.500 -0.2520 0.01366 0.00574 -0.0556 0.8820 0.2107
-4.250 -0.2234 0.01339 0.00549 -0.0557 0.8732 0.2271
-4.000 -0.1959 0.01314 0.00528 -0.0555 0.8637 0.2442
-3.750 -0.1676 0.01288 0.00506 -0.0554 0.8543 0.2625
-3.500 -0.1407 0.01266 0.00488 -0.0551 0.8436 0.2812
-3.250 -0.1123 0.01243 0.00468 -0.0551 0.8339 0.3016
-3.000 -0.0859 0.01224 0.00453 -0.0546 0.8219 0.3224
-2.750 -0.0586 0.01205 0.00437 -0.0544 0.8105 0.3447
-2.500 -0.0315 0.01185 0.00422 -0.0540 0.7988 0.3681
-2.250 -0.0051 0.01167 0.00410 -0.0536 0.7860 0.3935
-1.750 0.0480 0.01133 0.00389 -0.0527 0.7609 0.4536
-1.500 0.0738 0.01118 0.00383 -0.0521 0.7470 0.4876
-1.250 0.0998 0.01104 0.00378 -0.0515 0.7336 0.5231
-1.000 0.1257 0.01093 0.00374 -0.0509 0.7202 0.5589
-0.750 0.1516 0.01085 0.00371 -0.0502 0.7065 0.5946
-0.500 0.1773 0.01077 0.00371 -0.0495 0.6924 0.6297
-0.250 0.2029 0.01071 0.00373 -0.0488 0.6787 0.6637
0.000 0.2286 0.01068 0.00375 -0.0480 0.6653 0.6968
0.250 0.2542 0.01067 0.00378 -0.0472 0.6516 0.7297
0.500 0.2798 0.01067 0.00384 -0.0463 0.6379 0.7616
0.750 0.3057 0.01070 0.00392 -0.0455 0.6246 0.7922
1.000 0.3319 0.01077 0.00399 -0.0447 0.6118 0.8221
1.250 0.3591 0.01086 0.00409 -0.0442 0.5985 0.8493
1.500 0.3877 0.01097 0.00420 -0.0439 0.5855 0.8746
1.750 0.4173 0.01112 0.00430 -0.0440 0.5731 0.8971
2.000 0.4484 0.01127 0.00441 -0.0444 0.5602 0.9166
2.250 0.4813 0.01143 0.00454 -0.0452 0.5473 0.9332
2.500 0.5156 0.01160 0.00465 -0.0464 0.5346 0.9472
2.750 0.5503 0.01179 0.00477 -0.0477 0.5217 0.9597
3.000 0.5861 0.01196 0.00490 -0.0493 0.5081 0.9715
3.250 0.6252 0.01216 0.00505 -0.0517 0.4945 0.9823
3.500 0.6666 0.01235 0.00519 -0.0546 0.4807 0.9908
3.750 0.7052 0.01255 0.00532 -0.0570 0.4668 0.9973
4.000 0.7334 0.01271 0.00545 -0.0572 0.4534 1.0000
4.250 0.7536 0.01287 0.00557 -0.0558 0.4409 1.0000
4.500 0.7734 0.01306 0.00571 -0.0543 0.4282 1.0000
4.750 0.7931 0.01327 0.00585 -0.0527 0.4146 1.0000
5.000 0.8132 0.01347 0.00602 -0.0513 0.4004 1.0000
5.250 0.8332 0.01369 0.00621 -0.0498 0.3864 1.0000
5.500 0.8528 0.01393 0.00640 -0.0482 0.3719 1.0000
5.750 0.8721 0.01420 0.00661 -0.0466 0.3568 1.0000
6.000 0.8912 0.01449 0.00685 -0.0450 0.3411 1.0000
6.250 0.9104 0.01481 0.00711 -0.0434 0.3252 1.0000
6.500 0.9294 0.01515 0.00739 -0.0418 0.3087 1.0000
6.750 0.9483 0.01552 0.00769 -0.0402 0.2918 1.0000
7.000 0.9670 0.01592 0.00803 -0.0387 0.2747 1.0000
7.250 0.9854 0.01634 0.00840 -0.0371 0.2578 1.0000
7.500 1.0035 0.01680 0.00879 -0.0355 0.2412 1.0000
7.750 1.0212 0.01728 0.00922 -0.0339 0.2250 1.0000
8.000 1.0384 0.01779 0.00967 -0.0322 0.2095 1.0000
8.250 1.0550 0.01834 0.01016 -0.0305 0.1947 1.0000
8.500 1.0707 0.01891 0.01068 -0.0287 0.1807 1.0000
8.750 1.0853 0.01948 0.01121 -0.0266 0.1677 1.0000
9.000 1.0993 0.02008 0.01178 -0.0245 0.1557 1.0000
9.250 1.1129 0.02073 0.01241 -0.0225 0.1448 1.0000
9.500 1.1258 0.02144 0.01310 -0.0204 0.1349 1.0000
9.750 1.1384 0.02221 0.01384 -0.0185 0.1257 1.0000
10.000 1.1519 0.02296 0.01460 -0.0167 0.1173 1.0000
10.250 1.1638 0.02382 0.01546 -0.0149 0.1101 1.0000
10.500 1.1757 0.02472 0.01637 -0.0131 0.1033 1.0000
10.750 1.1873 0.02567 0.01734 -0.0115 0.0975 1.0000
11.000 1.1976 0.02673 0.01841 -0.0098 0.0920 1.0000
11.250 1.2083 0.02781 0.01953 -0.0083 0.0873 1.0000
11.500 1.2178 0.02900 0.02076 -0.0068 0.0828 1.0000
11.750 1.2264 0.03031 0.02210 -0.0054 0.0791 1.0000
12.000 1.2357 0.03162 0.02348 -0.0042 0.0753 1.0000
12.250 1.2417 0.03322 0.02510 -0.0029 0.0722 1.0000
12.500 1.2501 0.03471 0.02667 -0.0019 0.0692 1.0000
12.750 1.2568 0.03638 0.02841 -0.0009 0.0664 1.0000
13.000 1.2604 0.03838 0.03043 0.0000 0.0642 1.0000
13.250 1.2668 0.04020 0.03235 0.0006 0.0618 1.0000
13.500 1.2718 0.04222 0.03445 0.0012 0.0596 1.0000
13.750 1.2742 0.04453 0.03682 0.0017 0.0578 1.0000
14.000 1.2758 0.04699 0.03934 0.0020 0.0562 1.0000
14.250 1.2796 0.04931 0.04177 0.0022 0.0543 1.0000
14.500 1.2816 0.05186 0.04442 0.0023 0.0527 1.0000
14.750 1.2817 0.05470 0.04732 0.0022 0.0513 1.0000
15.000 1.2799 0.05784 0.05050 0.0019 0.0502 1.0000
15.250 1.2816 0.06064 0.05344 0.0016 0.0488 1.0000
15.500 1.2818 0.06367 0.05658 0.0012 0.0475 1.0000
15.750 1.2809 0.06692 0.05991 0.0007 0.0464 1.0000
16.000 1.2786 0.07039 0.06346 -0.0001 0.0454 1.0000
16.250 1.2749 0.07409 0.06720 -0.0010 0.0445 1.0000
16.500 1.2735 0.07755 0.07078 -0.0018 0.0435 1.0000
16.750 1.2716 0.08114 0.07449 -0.0027 0.0426 1.0000
17.000 1.2690 0.08490 0.07835 -0.0038 0.0416 1.0000
17.250 1.2657 0.08879 0.08234 -0.0050 0.0408 1.0000
17.500 1.2618 0.09279 0.08642 -0.0064 0.0401 1.0000
17.750 1.2577 0.09685 0.09052 -0.0078 0.0394 1.0000
18.000 1.2539 0.10093 0.09471 -0.0092 0.0387 1.0000
18.250 1.2499 0.10516 0.09908 -0.0108 0.0379 1.0000
18.500 1.2456 0.10946 0.10349 -0.0126 0.0371 1.0000
18.750 1.2410 0.11385 0.10799 -0.0145 0.0364 1.0000
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