NACA 2415 (n2415-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2415 (n2415-il) Reynolds number: 200,000 Max Cl/Cd: 64.16 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n2415-il-200000.txt Download as CSV file: xf-n2415-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 -0.7841 0.07840 0.07388 -0.0595 1.0000 0.0563
-14.000 -0.8778 0.06085 0.05586 -0.0730 1.0000 0.0548
-13.750 -0.9147 0.05409 0.04880 -0.0764 1.0000 0.0547
-13.500 -0.9374 0.04984 0.04432 -0.0769 1.0000 0.0549
-13.250 -0.9551 0.04665 0.04090 -0.0758 1.0000 0.0553
-13.000 -0.9710 0.04414 0.03818 -0.0731 1.0000 0.0557
-12.750 -0.9869 0.04216 0.03600 -0.0688 1.0000 0.0562
-12.500 -0.9983 0.04024 0.03384 -0.0647 1.0000 0.0568
-12.250 -1.0073 0.03850 0.03181 -0.0605 1.0000 0.0576
-12.000 -1.0083 0.03670 0.02981 -0.0572 1.0000 0.0585
-11.750 -0.9949 0.03556 0.02875 -0.0555 1.0000 0.0597
-11.500 -0.9867 0.03462 0.02777 -0.0529 1.0000 0.0609
-11.250 -0.9796 0.03357 0.02662 -0.0501 1.0000 0.0623
-11.000 -0.9739 0.03239 0.02524 -0.0470 1.0000 0.0637
-10.750 -0.9688 0.03126 0.02382 -0.0437 1.0000 0.0649
-10.500 -0.9557 0.02985 0.02244 -0.0418 1.0000 0.0664
-10.250 -0.9423 0.02910 0.02173 -0.0397 1.0000 0.0681
-10.000 -0.9303 0.02834 0.02088 -0.0374 1.0000 0.0701
-9.750 -0.9185 0.02753 0.01987 -0.0350 1.0000 0.0721
-9.500 -0.9048 0.02643 0.01869 -0.0329 1.0000 0.0741
-9.250 -0.8892 0.02571 0.01804 -0.0312 1.0000 0.0762
-9.000 -0.8740 0.02511 0.01739 -0.0293 1.0000 0.0788
-8.750 -0.8589 0.02453 0.01661 -0.0274 1.0000 0.0815
-8.500 -0.8421 0.02360 0.01575 -0.0259 1.0000 0.0842
-8.250 -0.8249 0.02311 0.01527 -0.0244 1.0000 0.0873
-8.000 -0.8074 0.02266 0.01468 -0.0228 1.0000 0.0908
-7.750 -0.7869 0.02189 0.01398 -0.0220 0.9995 0.0946
-7.500 -0.7482 0.02140 0.01345 -0.0246 0.9956 0.1003
-7.250 -0.7104 0.02070 0.01278 -0.0271 0.9919 0.1064
-7.000 -0.6729 0.02029 0.01228 -0.0293 0.9869 0.1136
-6.750 -0.6337 0.01964 0.01175 -0.0321 0.9830 0.1217
-6.500 -0.5979 0.01907 0.01119 -0.0340 0.9775 0.1305
-6.250 -0.5590 0.01869 0.01076 -0.0364 0.9723 0.1410
-6.000 -0.5168 0.01820 0.01034 -0.0396 0.9690 0.1537
-5.750 -0.4858 0.01770 0.00993 -0.0405 0.9613 0.1659
-5.500 -0.4457 0.01724 0.00954 -0.0431 0.9570 0.1816
-5.250 -0.4078 0.01683 0.00919 -0.0453 0.9523 0.1986
-5.000 -0.3745 0.01643 0.00886 -0.0465 0.9451 0.2164
-4.750 -0.3328 0.01601 0.00850 -0.0493 0.9413 0.2380
-4.500 -0.2887 0.01553 0.00816 -0.0527 0.9389 0.2617
-4.250 -0.2616 0.01521 0.00792 -0.0525 0.9290 0.2827
-4.000 -0.2213 0.01480 0.00758 -0.0549 0.9250 0.3094
-3.750 -0.1889 0.01440 0.00731 -0.0557 0.9181 0.3343
-3.500 -0.1565 0.01401 0.00702 -0.0564 0.9105 0.3619
-3.250 -0.1197 0.01353 0.00667 -0.0579 0.9060 0.3924
-3.000 -0.0944 0.01322 0.00648 -0.0572 0.8950 0.4223
-2.750 -0.0612 0.01277 0.00617 -0.0578 0.8889 0.4589
-2.500 -0.0365 0.01247 0.00602 -0.0568 0.8775 0.4958
-2.250 -0.0055 0.01206 0.00577 -0.0569 0.8704 0.5381
-2.000 0.0183 0.01181 0.00568 -0.0557 0.8579 0.5791
-1.750 0.0455 0.01153 0.00553 -0.0549 0.8478 0.6216
-1.500 0.0719 0.01129 0.00541 -0.0540 0.8364 0.6624
-1.250 0.0969 0.01112 0.00536 -0.0528 0.8238 0.7011
-1.000 0.1237 0.01096 0.00528 -0.0518 0.8124 0.7382
-0.750 0.1494 0.01086 0.00524 -0.0506 0.7995 0.7731
-0.500 0.1744 0.01082 0.00525 -0.0493 0.7855 0.8064
-0.250 0.2006 0.01082 0.00527 -0.0481 0.7724 0.8365
0.000 0.2279 0.01085 0.00526 -0.0471 0.7597 0.8648
0.250 0.2563 0.01094 0.00534 -0.0464 0.7450 0.8890
0.500 0.2869 0.01107 0.00542 -0.0462 0.7303 0.9108
0.750 0.3212 0.01122 0.00550 -0.0469 0.7161 0.9292
1.000 0.3597 0.01139 0.00556 -0.0485 0.7018 0.9440
1.250 0.4013 0.01155 0.00561 -0.0508 0.6874 0.9566
1.500 0.4447 0.01171 0.00569 -0.0538 0.6716 0.9681
1.750 0.4933 0.01182 0.00573 -0.0579 0.6557 0.9763
2.000 0.5396 0.01193 0.00575 -0.0617 0.6401 0.9855
2.250 0.5865 0.01202 0.00575 -0.0657 0.6247 0.9943
2.500 0.6283 0.01209 0.00572 -0.0687 0.6098 1.0000
2.750 0.6497 0.01215 0.00570 -0.0677 0.5966 1.0000
3.000 0.6703 0.01223 0.00574 -0.0665 0.5830 1.0000
3.250 0.6913 0.01234 0.00579 -0.0653 0.5702 1.0000
3.500 0.7126 0.01249 0.00583 -0.0641 0.5581 1.0000
3.750 0.7329 0.01260 0.00594 -0.0628 0.5446 1.0000
4.000 0.7535 0.01276 0.00605 -0.0614 0.5316 1.0000
4.250 0.7743 0.01294 0.00615 -0.0600 0.5191 1.0000
4.500 0.7948 0.01311 0.00628 -0.0586 0.5058 1.0000
4.750 0.8149 0.01328 0.00644 -0.0571 0.4920 1.0000
5.000 0.8352 0.01348 0.00660 -0.0556 0.4786 1.0000
5.250 0.8557 0.01371 0.00676 -0.0541 0.4654 1.0000
5.500 0.8756 0.01392 0.00693 -0.0525 0.4513 1.0000
5.750 0.8953 0.01413 0.00713 -0.0509 0.4366 1.0000
6.000 0.9149 0.01436 0.00735 -0.0493 0.4218 1.0000
6.250 0.9344 0.01461 0.00756 -0.0477 0.4068 1.0000
6.500 0.9537 0.01487 0.00778 -0.0460 0.3912 1.0000
6.750 0.9726 0.01516 0.00803 -0.0443 0.3749 1.0000
7.000 0.9914 0.01548 0.00830 -0.0427 0.3578 1.0000
7.250 1.0098 0.01582 0.00860 -0.0410 0.3403 1.0000
7.500 1.0278 0.01620 0.00894 -0.0392 0.3222 1.0000
7.750 1.0454 0.01662 0.00931 -0.0374 0.3038 1.0000
8.000 1.0622 0.01708 0.00972 -0.0356 0.2852 1.0000
8.250 1.0782 0.01760 0.01017 -0.0337 0.2666 1.0000
8.500 1.0932 0.01817 0.01067 -0.0316 0.2483 1.0000
8.750 1.1071 0.01879 0.01122 -0.0294 0.2306 1.0000
9.000 1.1195 0.01946 0.01181 -0.0271 0.2137 1.0000
9.250 1.1302 0.02016 0.01245 -0.0244 0.1982 1.0000
9.500 1.1408 0.02093 0.01316 -0.0219 0.1836 1.0000
9.750 1.1514 0.02175 0.01395 -0.0195 0.1702 1.0000
10.000 1.1617 0.02265 0.01482 -0.0172 0.1581 1.0000
10.250 1.1709 0.02366 0.01578 -0.0149 0.1477 1.0000
10.500 1.1787 0.02479 0.01683 -0.0126 0.1384 1.0000
10.750 1.1899 0.02577 0.01787 -0.0108 0.1294 1.0000
11.000 1.1977 0.02703 0.01908 -0.0088 0.1222 1.0000
11.250 1.2068 0.02821 0.02028 -0.0071 0.1153 1.0000
11.500 1.2147 0.02957 0.02165 -0.0053 0.1094 1.0000
11.750 1.2233 0.03088 0.02298 -0.0038 0.1039 1.0000
12.000 1.2304 0.03242 0.02450 -0.0022 0.0992 1.0000
12.250 1.2392 0.03380 0.02596 -0.0010 0.0946 1.0000
12.500 1.2457 0.03546 0.02754 0.0004 0.0908 1.0000
12.750 1.2540 0.03700 0.02921 0.0015 0.0871 1.0000
13.000 1.2615 0.03860 0.03085 0.0025 0.0837 1.0000
13.250 1.2698 0.04029 0.03243 0.0037 0.0806 1.0000
13.500 1.2760 0.04207 0.03440 0.0046 0.0779 1.0000
13.750 1.2826 0.04385 0.03625 0.0053 0.0751 1.0000
14.000 1.2905 0.04557 0.03792 0.0061 0.0728 1.0000
14.250 1.2975 0.04748 0.03991 0.0070 0.0705 1.0000
14.500 1.3019 0.04957 0.04214 0.0075 0.0684 1.0000
14.750 1.3077 0.05155 0.04416 0.0080 0.0663 1.0000
15.000 1.3181 0.05314 0.04568 0.0087 0.0644 1.0000
15.250 1.3220 0.05546 0.04814 0.0093 0.0628 1.0000
15.500 1.3227 0.05808 0.05094 0.0095 0.0613 1.0000
15.750 1.3256 0.06052 0.05348 0.0096 0.0597 1.0000
16.000 1.3313 0.06264 0.05562 0.0098 0.0583 1.0000
16.250 1.3455 0.06400 0.05688 0.0107 0.0566 1.0000
16.500 1.3387 0.06760 0.06072 0.0102 0.0557 1.0000
16.750 1.3343 0.07109 0.06442 0.0097 0.0546 1.0000
17.000 1.3304 0.07460 0.06810 0.0090 0.0536 1.0000
17.250 1.3288 0.07788 0.07150 0.0084 0.0526 1.0000
17.500 1.3314 0.08059 0.07424 0.0080 0.0516 1.0000
17.750 1.3475 0.08156 0.07510 0.0090 0.0504 1.0000
18.000 1.3339 0.08656 0.08035 0.0073 0.0498 1.0000
18.250 1.3168 0.09228 0.08633 0.0050 0.0493 1.0000
18.500 1.2992 0.09830 0.09260 0.0023 0.0488 1.0000
18.750 1.2802 0.10481 0.09935 -0.0008 0.0483 1.0000
19.000 1.2592 0.11193 0.10670 -0.0045 0.0479 1.0000
19.250 1.2332 0.12028 0.11530 -0.0093 0.0476 1.0000
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Polar data table (+)
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