NACA 4415 (naca4415-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4415 (naca4415-il) Reynolds number: 200,000 Max Cl/Cd: 68.24 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4415-il-200000-n5.txt Download as CSV file: xf-naca4415-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6039 0.08561 0.08117 -0.0677 1.0000 0.0243
-13.750 -0.6618 0.07329 0.06866 -0.0742 1.0000 0.0241
-13.500 -0.6989 0.06516 0.06037 -0.0780 1.0000 0.0238
-13.250 -0.7313 0.05806 0.05313 -0.0814 1.0000 0.0238
-13.000 -0.7598 0.05198 0.04692 -0.0841 1.0000 0.0238
-12.750 -0.7865 0.04713 0.04193 -0.0857 1.0000 0.0238
-12.500 -0.8061 0.04311 0.03775 -0.0873 0.9988 0.0238
-12.250 -0.8012 0.03966 0.03408 -0.0915 0.9935 0.0242
-12.000 -0.7975 0.03722 0.03143 -0.0925 0.9871 0.0247
-11.750 -0.7878 0.03526 0.02926 -0.0931 0.9819 0.0251
-11.500 -0.7771 0.03343 0.02721 -0.0928 0.9751 0.0257
-11.250 -0.7570 0.03179 0.02546 -0.0938 0.9712 0.0262
-11.000 -0.7439 0.03053 0.02413 -0.0928 0.9640 0.0268
-10.750 -0.7217 0.02922 0.02272 -0.0934 0.9598 0.0276
-10.500 -0.7027 0.02804 0.02140 -0.0931 0.9545 0.0286
-10.250 -0.6833 0.02695 0.02012 -0.0925 0.9488 0.0298
-10.000 -0.6578 0.02586 0.01899 -0.0933 0.9453 0.0309
-9.750 -0.6375 0.02498 0.01802 -0.0927 0.9399 0.0323
-9.500 -0.6159 0.02407 0.01696 -0.0921 0.9342 0.0339
-9.250 -0.5887 0.02312 0.01597 -0.0927 0.9309 0.0354
-9.000 -0.5580 0.02223 0.01497 -0.0938 0.9286 0.0375
-8.750 -0.5431 0.02158 0.01426 -0.0916 0.9199 0.0393
-8.500 -0.5143 0.02084 0.01344 -0.0922 0.9162 0.0423
-8.250 -0.4825 0.02006 0.01262 -0.0934 0.9135 0.0455
-8.000 -0.4626 0.01955 0.01202 -0.0919 0.9061 0.0489
-7.750 -0.4349 0.01894 0.01139 -0.0921 0.9012 0.0530
-7.500 -0.4014 0.01833 0.01074 -0.0935 0.8981 0.0585
-7.250 -0.3728 0.01784 0.01022 -0.0937 0.8930 0.0646
-7.000 -0.3482 0.01745 0.00976 -0.0931 0.8859 0.0710
-6.750 -0.3140 0.01699 0.00926 -0.0944 0.8819 0.0787
-6.500 -0.2813 0.01656 0.00883 -0.0955 0.8773 0.0864
-6.250 -0.2585 0.01625 0.00849 -0.0945 0.8689 0.0928
-6.000 -0.2238 0.01588 0.00805 -0.0958 0.8642 0.1006
-5.750 -0.1963 0.01557 0.00773 -0.0957 0.8571 0.1077
-5.500 -0.1678 0.01527 0.00739 -0.0958 0.8498 0.1147
-5.250 -0.1312 0.01495 0.00700 -0.0975 0.8448 0.1234
-5.000 -0.1095 0.01472 0.00678 -0.0962 0.8351 0.1304
-4.750 -0.0758 0.01445 0.00645 -0.0972 0.8287 0.1398
-4.500 -0.0513 0.01423 0.00624 -0.0965 0.8195 0.1482
-4.250 -0.0206 0.01398 0.00594 -0.0969 0.8118 0.1570
-4.000 0.0050 0.01379 0.00573 -0.0964 0.8027 0.1659
-3.750 0.0340 0.01357 0.00548 -0.0965 0.7942 0.1753
-3.500 0.0593 0.01342 0.00529 -0.0958 0.7847 0.1852
-3.250 0.0875 0.01322 0.00508 -0.0958 0.7758 0.1962
-3.000 0.1116 0.01309 0.00493 -0.0949 0.7656 0.2075
-2.500 0.1631 0.01283 0.00465 -0.0937 0.7458 0.2345
-2.250 0.1892 0.01271 0.00452 -0.0932 0.7360 0.2498
-2.000 0.2135 0.01260 0.00441 -0.0924 0.7254 0.2656
-1.750 0.2380 0.01251 0.00432 -0.0915 0.7152 0.2832
-1.500 0.2631 0.01242 0.00422 -0.0908 0.7049 0.3025
-1.250 0.2860 0.01233 0.00417 -0.0897 0.6943 0.3233
-1.000 0.3105 0.01224 0.00409 -0.0889 0.6843 0.3476
-0.750 0.3326 0.01214 0.00405 -0.0876 0.6736 0.3760
-0.500 0.3551 0.01202 0.00402 -0.0864 0.6638 0.4123
-0.250 0.3762 0.01187 0.00401 -0.0849 0.6536 0.4621
0.000 0.3958 0.01169 0.00404 -0.0831 0.6439 0.5290
0.250 0.4154 0.01152 0.00408 -0.0812 0.6345 0.6077
0.500 0.4354 0.01136 0.00415 -0.0792 0.6249 0.6833
0.750 0.4619 0.01125 0.00423 -0.0786 0.6157 0.7628
1.000 0.5197 0.01126 0.00445 -0.0846 0.6049 0.8585
1.250 0.5967 0.01148 0.00464 -0.0949 0.5939 0.9184
1.500 0.6474 0.01168 0.00476 -0.0996 0.5832 0.9477
1.750 0.6853 0.01189 0.00490 -0.1016 0.5737 0.9708
2.000 0.7228 0.01210 0.00502 -0.1037 0.5641 0.9884
2.250 0.7651 0.01230 0.00515 -0.1069 0.5541 0.9995
2.500 0.7854 0.01245 0.00521 -0.1054 0.5458 1.0000
2.750 0.8037 0.01258 0.00531 -0.1035 0.5373 1.0000
3.000 0.8222 0.01274 0.00540 -0.1016 0.5291 1.0000
3.250 0.8408 0.01289 0.00551 -0.0997 0.5208 1.0000
3.500 0.8593 0.01306 0.00563 -0.0978 0.5124 1.0000
3.750 0.8779 0.01324 0.00576 -0.0960 0.5044 1.0000
4.000 0.8965 0.01341 0.00590 -0.0941 0.4964 1.0000
4.250 0.9150 0.01361 0.00605 -0.0922 0.4885 1.0000
4.500 0.9332 0.01379 0.00622 -0.0903 0.4803 1.0000
4.750 0.9510 0.01401 0.00638 -0.0882 0.4721 1.0000
5.000 0.9675 0.01420 0.00656 -0.0860 0.4620 1.0000
5.250 0.9837 0.01443 0.00675 -0.0836 0.4522 1.0000
5.500 0.9996 0.01465 0.00695 -0.0813 0.4425 1.0000
5.750 1.0154 0.01488 0.00715 -0.0789 0.4334 1.0000
6.000 1.0302 0.01511 0.00736 -0.0763 0.4250 1.0000
6.250 1.0452 0.01534 0.00759 -0.0738 0.4167 1.0000
6.500 1.0593 0.01559 0.00782 -0.0712 0.4079 1.0000
6.750 1.0745 0.01584 0.00808 -0.0688 0.3994 1.0000
7.000 1.0885 0.01614 0.00836 -0.0662 0.3902 1.0000
7.250 1.1038 0.01642 0.00866 -0.0639 0.3811 1.0000
7.500 1.1174 0.01677 0.00897 -0.0614 0.3719 1.0000
7.750 1.1323 0.01709 0.00932 -0.0591 0.3617 1.0000
8.000 1.1459 0.01748 0.00969 -0.0567 0.3523 1.0000
8.250 1.1599 0.01788 0.01009 -0.0544 0.3420 1.0000
8.500 1.1733 0.01832 0.01053 -0.0521 0.3314 1.0000
8.750 1.1850 0.01883 0.01101 -0.0496 0.3206 1.0000
9.000 1.1981 0.01933 0.01153 -0.0474 0.3093 1.0000
9.250 1.2102 0.01989 0.01209 -0.0451 0.2982 1.0000
9.500 1.2206 0.02054 0.01271 -0.0426 0.2870 1.0000
9.750 1.2313 0.02122 0.01339 -0.0403 0.2753 1.0000
10.000 1.2417 0.02195 0.01412 -0.0381 0.2634 1.0000
10.250 1.2509 0.02277 0.01493 -0.0358 0.2523 1.0000
10.500 1.2582 0.02372 0.01584 -0.0334 0.2406 1.0000
10.750 1.2652 0.02475 0.01684 -0.0311 0.2274 1.0000
11.000 1.2723 0.02583 0.01790 -0.0290 0.2150 1.0000
11.250 1.2789 0.02698 0.01904 -0.0269 0.2039 1.0000
11.500 1.2844 0.02827 0.02030 -0.0249 0.1943 1.0000
11.750 1.2921 0.02947 0.02153 -0.0232 0.1851 1.0000
12.000 1.2981 0.03082 0.02289 -0.0215 0.1770 1.0000
12.250 1.3040 0.03224 0.02433 -0.0199 0.1691 1.0000
12.500 1.3099 0.03371 0.02583 -0.0184 0.1621 1.0000
12.750 1.3154 0.03527 0.02741 -0.0171 0.1556 1.0000
13.000 1.3199 0.03694 0.02912 -0.0158 0.1495 1.0000
13.250 1.3257 0.03859 0.03082 -0.0146 0.1436 1.0000
13.500 1.3276 0.04061 0.03285 -0.0135 0.1383 1.0000
13.750 1.3340 0.04230 0.03462 -0.0126 0.1327 1.0000
14.000 1.3368 0.04437 0.03673 -0.0117 0.1277 1.0000
14.250 1.3399 0.04647 0.03888 -0.0110 0.1228 1.0000
14.500 1.3435 0.04858 0.04107 -0.0104 0.1177 1.0000
14.750 1.3430 0.05114 0.04365 -0.0098 0.1133 1.0000
15.000 1.3474 0.05328 0.04589 -0.0094 0.1082 1.0000
15.250 1.3473 0.05593 0.04859 -0.0090 0.1034 1.0000
15.500 1.3482 0.05855 0.05128 -0.0088 0.0987 1.0000
15.750 1.3484 0.06128 0.05409 -0.0087 0.0940 1.0000
16.000 1.3460 0.06438 0.05723 -0.0087 0.0897 1.0000
16.250 1.3456 0.06731 0.06024 -0.0088 0.0849 1.0000
16.500 1.3409 0.07082 0.06378 -0.0091 0.0811 1.0000
16.750 1.3401 0.07388 0.06694 -0.0093 0.0772 1.0000
17.000 1.3354 0.07750 0.07061 -0.0098 0.0735 1.0000
17.250 1.3310 0.08113 0.07430 -0.0103 0.0701 1.0000
17.500 1.3270 0.08476 0.07801 -0.0110 0.0671 1.0000
17.750 1.3207 0.08877 0.08208 -0.0118 0.0646 1.0000
18.000 1.3156 0.09262 0.08601 -0.0126 0.0623 1.0000
18.250 1.3114 0.09641 0.08989 -0.0135 0.0599 1.0000
18.500 1.3053 0.10052 0.09407 -0.0146 0.0579 1.0000
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Polar data table (+)
Polar graphs
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