NACA 4415 (naca4415-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 4415 (naca4415-il) Reynolds number: 200,000 Max Cl/Cd: 71.07 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4415-il-200000.txt Download as CSV file: xf-naca4415-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4415
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7375 0.05384 0.04943 -0.0813 1.0000 0.0385
-11.500 -0.7689 0.05201 0.04755 -0.0769 1.0000 0.0384
-11.250 -0.7971 0.05069 0.04619 -0.0712 1.0000 0.0382
-11.000 -0.8277 0.04848 0.04379 -0.0661 1.0000 0.0383
-10.750 -0.8374 0.04420 0.03894 -0.0664 0.9950 0.0386
-10.500 -0.8169 0.04161 0.03631 -0.0680 0.9903 0.0394
-10.250 -0.7937 0.03954 0.03411 -0.0696 0.9853 0.0403
-10.000 -0.7731 0.03727 0.03158 -0.0707 0.9799 0.0412
-9.750 -0.7534 0.03485 0.02878 -0.0714 0.9739 0.0422
-9.500 -0.7325 0.03256 0.02598 -0.0718 0.9685 0.0435
-9.250 -0.7092 0.03086 0.02420 -0.0721 0.9627 0.0447
-9.000 -0.6756 0.02980 0.02308 -0.0740 0.9591 0.0468
-8.750 -0.6540 0.02864 0.02163 -0.0735 0.9524 0.0489
-8.500 -0.6244 0.02743 0.02044 -0.0745 0.9476 0.0513
-8.250 -0.5888 0.02639 0.01923 -0.0764 0.9446 0.0546
-8.000 -0.5690 0.02541 0.01819 -0.0752 0.9372 0.0572
-7.750 -0.5366 0.02469 0.01740 -0.0764 0.9325 0.0615
-7.500 -0.4995 0.02383 0.01655 -0.0784 0.9298 0.0666
-7.250 -0.4791 0.02317 0.01574 -0.0771 0.9218 0.0713
-7.000 -0.4464 0.02256 0.01515 -0.0782 0.9172 0.0776
-6.750 -0.4082 0.02189 0.01448 -0.0803 0.9144 0.0858
-6.500 -0.3840 0.02138 0.01396 -0.0796 0.9075 0.0933
-6.250 -0.3535 0.02083 0.01338 -0.0801 0.9020 0.1026
-6.000 -0.3151 0.02029 0.01278 -0.0821 0.8990 0.1135
-5.750 -0.2735 0.01984 0.01226 -0.0846 0.8971 0.1244
-5.500 -0.2550 0.01944 0.01196 -0.0828 0.8878 0.1318
-5.250 -0.2176 0.01887 0.01133 -0.0844 0.8843 0.1420
-5.000 -0.1751 0.01840 0.01079 -0.0871 0.8820 0.1528
-4.750 -0.1301 0.01774 0.01020 -0.0904 0.8803 0.1643
-4.500 -0.1107 0.01743 0.00986 -0.0885 0.8708 0.1729
-4.250 -0.0706 0.01700 0.00939 -0.0907 0.8669 0.1852
-4.000 -0.0277 0.01635 0.00880 -0.0935 0.8640 0.1983
-3.750 -0.0012 0.01596 0.00844 -0.0930 0.8562 0.2093
-3.500 0.0329 0.01553 0.00799 -0.0940 0.8498 0.2232
-3.250 0.0755 0.01501 0.00748 -0.0966 0.8458 0.2401
-3.000 0.0966 0.01478 0.00729 -0.0950 0.8355 0.2542
-2.750 0.1345 0.01434 0.00686 -0.0968 0.8295 0.2742
-2.500 0.1588 0.01408 0.00666 -0.0958 0.8197 0.2927
-2.250 0.1923 0.01368 0.00632 -0.0967 0.8122 0.3162
-2.000 0.2159 0.01343 0.00615 -0.0957 0.8020 0.3395
-1.750 0.2480 0.01309 0.00586 -0.0962 0.7938 0.3714
-1.500 0.2686 0.01284 0.00576 -0.0946 0.7828 0.4049
-1.250 0.2987 0.01244 0.00554 -0.0948 0.7747 0.4586
-1.000 0.3138 0.01214 0.00554 -0.0920 0.7628 0.5303
-0.750 0.3355 0.01175 0.00551 -0.0902 0.7537 0.6413
-0.500 0.3572 0.01144 0.00554 -0.0883 0.7430 0.7450
-0.250 0.4150 0.01130 0.00564 -0.0937 0.7333 0.8585
0.000 0.4946 0.01141 0.00568 -0.1038 0.7231 0.9166
0.250 0.5482 0.01162 0.00580 -0.1087 0.7114 0.9448
0.500 0.5978 0.01182 0.00585 -0.1128 0.7011 0.9650
0.750 0.6477 0.01200 0.00592 -0.1171 0.6893 0.9823
1.000 0.7041 0.01211 0.00592 -0.1231 0.6774 0.9950
1.250 0.7431 0.01215 0.00581 -0.1256 0.6669 1.0000
1.500 0.7571 0.01222 0.00583 -0.1230 0.6559 1.0000
1.750 0.7759 0.01232 0.00584 -0.1213 0.6462 1.0000
2.000 0.7938 0.01242 0.00586 -0.1193 0.6362 1.0000
2.250 0.8120 0.01256 0.00594 -0.1174 0.6264 1.0000
2.500 0.8324 0.01270 0.00598 -0.1159 0.6171 1.0000
2.750 0.8501 0.01287 0.00611 -0.1139 0.6074 1.0000
3.000 0.8721 0.01303 0.00617 -0.1127 0.5985 1.0000
3.250 0.8891 0.01321 0.00635 -0.1105 0.5888 1.0000
3.500 0.9120 0.01340 0.00642 -0.1094 0.5803 1.0000
3.750 0.9285 0.01359 0.00662 -0.1071 0.5708 1.0000
4.000 0.9520 0.01380 0.00672 -0.1062 0.5626 1.0000
4.250 0.9683 0.01400 0.00695 -0.1038 0.5532 1.0000
4.500 0.9915 0.01421 0.00705 -0.1029 0.5446 1.0000
4.750 1.0062 0.01439 0.00727 -0.1002 0.5344 1.0000
5.000 1.0274 0.01461 0.00740 -0.0988 0.5251 1.0000
5.250 1.0425 0.01479 0.00761 -0.0962 0.5150 1.0000
5.500 1.0635 0.01503 0.00779 -0.0948 0.5065 1.0000
5.750 1.0794 0.01523 0.00801 -0.0923 0.4971 1.0000
6.000 1.0997 0.01548 0.00822 -0.0908 0.4887 1.0000
6.250 1.1153 0.01570 0.00846 -0.0884 0.4795 1.0000
6.500 1.1343 0.01596 0.00867 -0.0867 0.4708 1.0000
6.750 1.1495 0.01618 0.00893 -0.0841 0.4615 1.0000
7.000 1.1671 0.01645 0.00918 -0.0821 0.4526 1.0000
7.250 1.1814 0.01668 0.00942 -0.0795 0.4431 1.0000
7.500 1.1962 0.01696 0.00971 -0.0770 0.4336 1.0000
7.750 1.2108 0.01723 0.00996 -0.0745 0.4242 1.0000
8.000 1.2209 0.01751 0.01028 -0.0711 0.4145 1.0000
8.250 1.2351 0.01782 0.01051 -0.0685 0.4051 1.0000
8.500 1.2409 0.01809 0.01087 -0.0643 0.3944 1.0000
8.750 1.2523 0.01844 0.01120 -0.0614 0.3842 1.0000
9.000 1.2622 0.01881 0.01155 -0.0582 0.3734 1.0000
9.250 1.2709 0.01922 0.01201 -0.0549 0.3617 1.0000
9.500 1.2802 0.01969 0.01246 -0.0519 0.3501 1.0000
9.750 1.2893 0.02023 0.01294 -0.0489 0.3384 1.0000
10.000 1.2965 0.02080 0.01356 -0.0458 0.3254 1.0000
10.250 1.3029 0.02147 0.01422 -0.0427 0.3118 1.0000
10.500 1.3091 0.02222 0.01496 -0.0397 0.2983 1.0000
10.750 1.3140 0.02308 0.01578 -0.0367 0.2847 1.0000
11.000 1.3186 0.02405 0.01669 -0.0338 0.2717 1.0000
11.250 1.3239 0.02507 0.01769 -0.0312 0.2591 1.0000
11.500 1.3299 0.02613 0.01877 -0.0289 0.2472 1.0000
11.750 1.3354 0.02729 0.01992 -0.0266 0.2366 1.0000
12.000 1.3393 0.02860 0.02116 -0.0243 0.2266 1.0000
12.250 1.3456 0.02983 0.02245 -0.0224 0.2167 1.0000
12.500 1.3500 0.03124 0.02382 -0.0204 0.2083 1.0000
12.750 1.3557 0.03261 0.02525 -0.0187 0.1998 1.0000
13.000 1.3601 0.03413 0.02676 -0.0171 0.1922 1.0000
13.250 1.3648 0.03567 0.02834 -0.0155 0.1847 1.0000
13.500 1.3688 0.03732 0.02999 -0.0141 0.1780 1.0000
13.750 1.3728 0.03903 0.03178 -0.0128 0.1710 1.0000
14.000 1.3757 0.04086 0.03358 -0.0115 0.1649 1.0000
14.250 1.3789 0.04277 0.03561 -0.0105 0.1581 1.0000
14.500 1.3802 0.04483 0.03759 -0.0093 0.1521 1.0000
14.750 1.3824 0.04698 0.03990 -0.0086 0.1457 1.0000
15.000 1.3820 0.04935 0.04223 -0.0078 0.1398 1.0000
15.250 1.3824 0.05178 0.04478 -0.0072 0.1334 1.0000
15.500 1.3808 0.05445 0.04746 -0.0067 0.1275 1.0000
15.750 1.3796 0.05717 0.05026 -0.0063 0.1214 1.0000
16.000 1.3767 0.06013 0.05326 -0.0060 0.1156 1.0000
16.250 1.3738 0.06315 0.05632 -0.0058 0.1097 1.0000
16.500 1.3703 0.06636 0.05959 -0.0059 0.1043 1.0000
16.750 1.3678 0.06940 0.06264 -0.0058 0.0995 1.0000
17.000 1.3640 0.07279 0.06612 -0.0061 0.0945 1.0000
17.250 1.3615 0.07584 0.06910 -0.0062 0.0904 1.0000
17.500 1.3587 0.07925 0.07266 -0.0066 0.0865 1.0000
17.750 1.3568 0.08245 0.07590 -0.0070 0.0832 1.0000
18.000 1.3575 0.08511 0.07852 -0.0069 0.0802 1.0000
18.250 1.3555 0.08846 0.08200 -0.0075 0.0774 1.0000
18.500 1.3549 0.09156 0.08516 -0.0080 0.0749 1.0000
18.750 1.3582 0.09387 0.08740 -0.0080 0.0724 1.0000
19.000 1.3572 0.09707 0.09072 -0.0086 0.0703 1.0000
19.250 1.3551 0.10050 0.09428 -0.0094 0.0683 1.0000
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Polar data table (+)
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