NACA 4415 (naca4415-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4415 (naca4415-il) Reynolds number: 500,000 Max Cl/Cd: 90.39 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4415-il-500000-n5.txt Download as CSV file: xf-naca4415-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7406 0.08436 0.08072 -0.0700 1.0000 0.0148
-15.500 -0.7675 0.07768 0.07397 -0.0729 1.0000 0.0148
-15.250 -0.8007 0.07032 0.06651 -0.0762 1.0000 0.0149
-15.000 -0.8372 0.06289 0.05898 -0.0793 1.0000 0.0148
-14.750 -0.8787 0.05492 0.05088 -0.0826 1.0000 0.0147
-14.500 -0.9121 0.04605 0.04183 -0.0887 0.9993 0.0146
-14.250 -0.9198 0.03781 0.03333 -0.0993 0.9963 0.0147
-14.000 -0.9170 0.03334 0.02867 -0.1053 0.9927 0.0149
-13.750 -0.9113 0.03073 0.02591 -0.1075 0.9882 0.0151
-13.500 -0.8995 0.02885 0.02390 -0.1088 0.9845 0.0152
-13.250 -0.8890 0.02742 0.02234 -0.1085 0.9801 0.0155
-13.000 -0.8771 0.02626 0.02107 -0.1076 0.9748 0.0158
-12.750 -0.8565 0.02512 0.01981 -0.1081 0.9720 0.0161
-12.500 -0.8435 0.02399 0.01860 -0.1068 0.9664 0.0163
-12.250 -0.8244 0.02291 0.01744 -0.1066 0.9621 0.0166
-12.000 -0.8001 0.02196 0.01643 -0.1070 0.9596 0.0171
-11.750 -0.7735 0.02109 0.01548 -0.1078 0.9579 0.0175
-11.500 -0.7591 0.02045 0.01476 -0.1058 0.9508 0.0180
-11.250 -0.7342 0.01970 0.01393 -0.1059 0.9476 0.0185
-11.000 -0.7061 0.01899 0.01313 -0.1066 0.9453 0.0192
-10.750 -0.6796 0.01825 0.01236 -0.1070 0.9422 0.0199
-10.500 -0.6594 0.01769 0.01174 -0.1058 0.9358 0.0206
-10.250 -0.6297 0.01709 0.01106 -0.1066 0.9323 0.0215
-10.000 -0.5955 0.01648 0.01038 -0.1083 0.9299 0.0225
-9.750 -0.5687 0.01592 0.00979 -0.1085 0.9246 0.0235
-9.500 -0.5408 0.01543 0.00924 -0.1088 0.9187 0.0248
-9.250 -0.5074 0.01492 0.00866 -0.1102 0.9146 0.0262
-9.000 -0.4795 0.01446 0.00816 -0.1105 0.9087 0.0278
-8.750 -0.4519 0.01408 0.00772 -0.1106 0.9018 0.0296
-8.500 -0.4195 0.01361 0.00722 -0.1117 0.8964 0.0321
-8.250 -0.3955 0.01328 0.00684 -0.1110 0.8880 0.0344
-8.000 -0.3660 0.01290 0.00642 -0.1115 0.8808 0.0373
-7.750 -0.3409 0.01259 0.00607 -0.1110 0.8725 0.0404
-7.500 -0.3136 0.01228 0.00573 -0.1109 0.8644 0.0445
-7.000 -0.2623 0.01174 0.00514 -0.1100 0.8471 0.0553
-6.750 -0.2375 0.01151 0.00489 -0.1094 0.8383 0.0615
-6.500 -0.2119 0.01130 0.00465 -0.1089 0.8294 0.0682
-6.250 -0.1874 0.01111 0.00445 -0.1081 0.8203 0.0744
-6.000 -0.1619 0.01094 0.00425 -0.1075 0.8109 0.0811
-5.750 -0.1377 0.01079 0.00407 -0.1067 0.8017 0.0874
-5.250 -0.0886 0.01052 0.00373 -0.1051 0.7826 0.0988
-5.000 -0.0641 0.01040 0.00357 -0.1043 0.7731 0.1044
-4.750 -0.0400 0.01029 0.00344 -0.1034 0.7628 0.1102
-4.500 -0.0160 0.01018 0.00330 -0.1025 0.7530 0.1164
-4.250 0.0081 0.01010 0.00317 -0.1016 0.7426 0.1231
-4.000 0.0317 0.00999 0.00306 -0.1006 0.7320 0.1319
-3.500 0.0790 0.00984 0.00286 -0.0986 0.7105 0.1483
-3.250 0.1026 0.00979 0.00276 -0.0975 0.6999 0.1557
-3.000 0.1258 0.00973 0.00268 -0.0964 0.6886 0.1643
-2.750 0.1494 0.00968 0.00260 -0.0954 0.6779 0.1730
-2.500 0.1724 0.00964 0.00254 -0.0943 0.6672 0.1827
-2.250 0.1958 0.00959 0.00248 -0.0932 0.6561 0.1925
-1.750 0.2419 0.00953 0.00239 -0.0909 0.6353 0.2163
-1.500 0.2651 0.00951 0.00236 -0.0899 0.6251 0.2288
-1.000 0.3111 0.00948 0.00232 -0.0876 0.6052 0.2578
-0.750 0.3335 0.00947 0.00231 -0.0864 0.5957 0.2731
-0.500 0.3564 0.00945 0.00231 -0.0852 0.5860 0.2907
-0.250 0.3787 0.00944 0.00231 -0.0840 0.5772 0.3086
0.000 0.4015 0.00942 0.00232 -0.0828 0.5681 0.3288
0.500 0.4453 0.00935 0.00236 -0.0802 0.5511 0.3829
0.750 0.4657 0.00931 0.00239 -0.0786 0.5430 0.4225
1.000 0.4863 0.00919 0.00243 -0.0771 0.5351 0.4764
1.250 0.5045 0.00909 0.00249 -0.0750 0.5275 0.5430
1.500 0.5222 0.00895 0.00256 -0.0728 0.5201 0.6138
1.750 0.5388 0.00886 0.00263 -0.0703 0.5124 0.6720
2.000 0.5552 0.00876 0.00270 -0.0677 0.5054 0.7335
2.250 0.5731 0.00863 0.00280 -0.0654 0.4977 0.8084
2.500 0.6911 0.00889 0.00327 -0.0852 0.4844 0.9283
2.750 0.7566 0.00920 0.00351 -0.0934 0.4739 0.9585
3.000 0.7904 0.00938 0.00368 -0.0947 0.4659 0.9784
3.250 0.8212 0.00960 0.00383 -0.0954 0.4574 0.9903
3.500 0.8570 0.00977 0.00398 -0.0972 0.4493 0.9971
3.750 0.8899 0.00999 0.00412 -0.0984 0.4384 1.0000
4.000 0.9066 0.01013 0.00422 -0.0961 0.4270 1.0000
4.250 0.9225 0.01030 0.00433 -0.0937 0.4168 1.0000
4.500 0.9378 0.01044 0.00444 -0.0911 0.4086 1.0000
4.750 0.9530 0.01058 0.00456 -0.0884 0.4018 1.0000
5.000 0.9688 0.01073 0.00468 -0.0859 0.3934 1.0000
5.250 0.9840 0.01090 0.00482 -0.0834 0.3851 1.0000
5.500 1.0006 0.01107 0.00497 -0.0811 0.3768 1.0000
5.750 1.0166 0.01127 0.00514 -0.0787 0.3689 1.0000
6.000 1.0334 0.01147 0.00531 -0.0765 0.3592 1.0000
6.250 1.0500 0.01170 0.00551 -0.0744 0.3503 1.0000
6.500 1.0667 0.01195 0.00573 -0.0722 0.3409 1.0000
6.750 1.0841 0.01219 0.00595 -0.0703 0.3324 1.0000
7.000 1.1001 0.01249 0.00621 -0.0681 0.3222 1.0000
7.250 1.1174 0.01277 0.00647 -0.0662 0.3118 1.0000
7.500 1.1332 0.01311 0.00677 -0.0641 0.3005 1.0000
7.750 1.1487 0.01348 0.00710 -0.0620 0.2895 1.0000
8.000 1.1653 0.01383 0.00743 -0.0601 0.2785 1.0000
8.250 1.1801 0.01427 0.00782 -0.0580 0.2659 1.0000
8.500 1.1947 0.01473 0.00824 -0.0559 0.2548 1.0000
8.750 1.2087 0.01524 0.00870 -0.0538 0.2421 1.0000
9.000 1.2226 0.01576 0.00919 -0.0517 0.2292 1.0000
9.250 1.2355 0.01636 0.00973 -0.0495 0.2156 1.0000
9.500 1.2471 0.01704 0.01035 -0.0473 0.2013 1.0000
9.750 1.2584 0.01777 0.01101 -0.0451 0.1872 1.0000
10.000 1.2702 0.01849 0.01169 -0.0430 0.1762 1.0000
10.250 1.2814 0.01927 0.01242 -0.0409 0.1661 1.0000
10.500 1.2947 0.01996 0.01312 -0.0392 0.1580 1.0000
10.750 1.3054 0.02082 0.01395 -0.0373 0.1492 1.0000
11.000 1.3182 0.02159 0.01473 -0.0356 0.1432 1.0000
11.250 1.3291 0.02249 0.01562 -0.0339 0.1373 1.0000
11.500 1.3416 0.02333 0.01648 -0.0324 0.1321 1.0000
11.750 1.3519 0.02432 0.01748 -0.0307 0.1267 1.0000
12.000 1.3630 0.02530 0.01848 -0.0292 0.1216 1.0000
12.250 1.3729 0.02639 0.01958 -0.0277 0.1164 1.0000
12.500 1.3823 0.02754 0.02075 -0.0263 0.1119 1.0000
12.750 1.3925 0.02867 0.02192 -0.0250 0.1071 1.0000
13.000 1.3999 0.03004 0.02330 -0.0236 0.1023 1.0000
13.250 1.4089 0.03133 0.02463 -0.0224 0.0977 1.0000
13.500 1.4155 0.03285 0.02617 -0.0211 0.0925 1.0000
13.750 1.4220 0.03442 0.02776 -0.0200 0.0873 1.0000
14.000 1.4267 0.03620 0.02955 -0.0188 0.0819 1.0000
14.250 1.4313 0.03804 0.03142 -0.0178 0.0766 1.0000
14.500 1.4339 0.04012 0.03351 -0.0169 0.0716 1.0000
14.750 1.4377 0.04214 0.03557 -0.0160 0.0672 1.0000
15.000 1.4390 0.04445 0.03791 -0.0153 0.0631 1.0000
15.250 1.4412 0.04674 0.04024 -0.0146 0.0592 1.0000
15.500 1.4409 0.04934 0.04288 -0.0141 0.0559 1.0000
15.750 1.4426 0.05179 0.04538 -0.0137 0.0532 1.0000
16.000 1.4415 0.05459 0.04823 -0.0133 0.0504 1.0000
16.250 1.4406 0.05743 0.05112 -0.0131 0.0482 1.0000
16.500 1.4400 0.06030 0.05406 -0.0130 0.0462 1.0000
16.750 1.4379 0.06339 0.05721 -0.0130 0.0446 1.0000
17.000 1.4346 0.06666 0.06055 -0.0131 0.0431 1.0000
17.250 1.4337 0.06970 0.06367 -0.0133 0.0417 1.0000
17.500 1.4312 0.07298 0.06702 -0.0136 0.0405 1.0000
17.750 1.4274 0.07648 0.07060 -0.0140 0.0394 1.0000
18.000 1.4221 0.08021 0.07439 -0.0145 0.0385 1.0000
18.250 1.4173 0.08393 0.07820 -0.0151 0.0377 1.0000
18.500 1.4145 0.08742 0.08177 -0.0157 0.0369 1.0000
18.750 1.4107 0.09108 0.08552 -0.0165 0.0361 1.0000
19.000 1.4053 0.09500 0.08953 -0.0174 0.0354 1.0000
19.250 1.3988 0.09910 0.09371 -0.0184 0.0346 1.0000
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